Patent Publication Number: US-2011061612-A1

Title: Space engine including the haase cycle with energy recovery cooling

Description:
RELATED APPLICATION DATA 
     This application claims priority on U.S. Provisional Application 61 /004,326 filed Nov. 26, 2007. 
    
    
     BACKGROUND OF THE INVENTION 
     1. Field of the Invention 
     The instant invention relates to improved methods, systems, processes and apparatus for the combustion of hydrogen (H 2 ) with oxygen (O 2 ), wherein the H 2  and O 2  are obtained from at least one storage tank or obtained by electrolysis of water (H 2 O). The instant invention is based upon the chemistry of H 2 O incorporating H 2  as the fuel and O 2  as the oxidizer. The instant invention does not require a hydrocarbon fuel source. H 2 O is the primary product of combustion while in many embodiments of the instant invention, H 2 O is separated into H 2  and O 2 , thereby making H 2 O an efficient method of storing fuel and oxidizer, e.g. potential energy. 
     Applications of the instant invention include: furnaces, combustion engines, internal combustion engines, turbine combustion engines, heating or any combustion engine, method, system or apparatus wherein mechanical, electrical or heat energy is created. The instant invention contains embodiments wherein Nitrogen (N 2 ) and Argon (Ar) are partially or totally removed from the fuel mixture to improve the energy output of combustion. 
     The discovered instant invention comprises improved combustion thermodynamics, thereby significantly improving the power and efficiency of combustion. Further, the discovered instant invention relates to improved combustion wherein H 2 O is added to the combustion chamber, thereby utilizing H 2 O during combustion as a heat sink, as well as the resultant steam energy as an energy source. The discovered instant invention incorporates embodiments wherein the steam produced by combustion: 1) maintains the power output of combustion, 2) provides method(s) of energy transfer, 3) provides an efficient method of energy recycle, 4) provides power through steam, and 5) cools the combustion chamber. Steam presents a potential (reusable) energy source, both from the available kinetic and the available heat energy, as well as the conversion of the steam into H 2  and O 2 . 
     The discovered instant invention relates to generating electricity (electrical energy). Two means of generating electricity are discovered. The first places a steam turbine in the exhaust of a combustion engine of the instant invention, wherein said steam turbine is driven by steam produced in combustion, and wherein said steam turbine turns a generator (the term generator is used herein to define either a generator, an alternator or a dynamo); and wherein at least a portion of said steam energy is converted into said electricity. The second places a generator to receive the mechanical rotating energy output of a combustion engine of the instant invention, wherein at least a portion of said mechanical rotating energy is converted by the generator into electricity. 
     The instant invention relates to combustion, wherein the thermodynamics of the Otto Cycle are improved providing improved combustion efficiency and power output, thereby producing the Haase Cycle. 
     The instant invention relates to the combustion of H 2  with O 2 , wherein said combustion powers a liquefaction unit for the storage of said H 2  and/or of said O 2 . 
     Finally, the instant invention relates to applications of producing mechanical or electrical energy, as well as improved hydrogen and/or oxygen storage in applications which at an altitude above the surface of the earth. 
     BACKGROUND OF THE INVENTION 
     Mankind, has over the centuries, developed many forms of energy, along with many forms of transportation. In the modem economy, energy is needed to literally “fuel” the economy. Energy heats homes, factories and offices, provides electrical power, powers manufacturing facilities, and provides for the transportation of goods and of people. During the 19′th and 20′th centuries, mankind developed fossil fuels into reliable and inexpensive energy sources. Today, fossil fuels are used in transportation, manufacturing, electricity generation and heating. This use has caused the combustion products from fossil fuels to be a major source of air and H 2 O pollution. 
     Fossil fuels (hydrocarbons) are used as a fuel along with air as an oxidant to generate combustion energy. Hydrocarbons are either: petroleum distillates such as gasoline, diesel, fuel oil, jet fuel and kerosene; fermentation distillates such as methanol and ethanol; or natural products such as methane, ethane, propane, butane, coal and wood. However, excess hydrocarbon combustion interferes with nature. The products of hydrocarbon combustion were thought to work in concert with nature&#39;s O 2 -carbon cycle, wherein CO 2  is recycled by plant life photosynthesis back into O 2 . However, excess CO 2 , e.g. excess combustion, upsets the environment. The combustion of a hydrocarbon can be approximated by: 
       C n H 2n+2 +(3/2n+½)O 2 →nCO 2 +(n+1)H 2 O+Energy
 
     More specifically, for gasoline (2,2,4 trimethyl pentane or n-Octane): 
       gasoline (n-Octane)+12-½O 2 →8CO 2 +9H 2 O+1,300 kcal
 
     And, for natural gas (methane): 
       CH 4 +3O 2 →CO 2 +2H 2 O+213 kcal
 
     So, oxides of carbon (CO X , CO and/or CO 2 ) are produced by the combustion of fossil fuels. It is generally believed among scientists that global warming is a result of a buildup of CO X  in the Earth&#39;s atmosphere. While photosynthesis will naturally turn CO 2  back into O 2 , man-made production of CO 2  in combination with significant deforestation have left earth&#39;s plant life incapable of converting enough of manmade CO 2  back into O 2 . This is while CO, an incomplete combustion by-product, is toxic to all human, animal and plant life. 
     In addition, hydrocarbon combustion with air creates NO X  (NO, NO 2  and NO 3 ); NO X  retards photosynthesis, while being toxic to all human, animal and plant life. This is while the formation of NO X  is endothermic, thereby lessening combustion efficiency. Once formed, NO X  further reacts with O 2  in the air to form ozone (O 3 ). O 3  is toxic to all human, animal and plant life. O 3  does protect the earth in the upper atmosphere from harmful U/V radiation; however, at the surface, O 3  is toxic to all life. 
     There have been many previous attempts to produce a combustion engine that would operate with H 2  as the fuel and air as the oxidant. Those attempts had as difficulties: higher combustion temperatures, reduced available torque, increased NO X  formation, a lack of H 2  storage capacity, excessive heat and cost of operation. Jet propulsion applications with H 2  as the fuel have had as difficulties: high combustion temperatures, lack of available thrust and a low altitude ceiling, thereby limiting jet propulsion use to kerosene. This is while, as compared to kerosene, H 2  has about three times the available combustion energy per pound. 
     Previous and current attempts to produce a fuel cell that would operate on H 2  and air or O 2 , as well as on a hydrocarbon and air demonstrate limitations. The capital investment to power output ratio for fuel cells is 300 to 500 percent of that for traditional hydrocarbon combustion. The available power and/or torque to engine mass available from a fuel cell are much lower than that of a combustion engine. Also, the maintenance requirement of fuel cells is 100 to 300 percent of that for a combustion engine. 
     Prior to this instant invention, previous work in the Water Combustion Technology (WCT) and the Haase Cycle is referenced herein in U.S. application Ser. No. 10/790,316, PCT/US 03/11250, PCT/US 03/41719 and PCT/US06/048057. 
     Previous work to develop a combustion engine prior to the WCT and the Haase Cycle that would operate on fuel(s) other than hydrocarbon(s) is referenced herein in U.S. Pat. No. 2,406,605; U.S. Pat. No. 3,459,953: U.S. Pat. No. 3,884,262, U.S. Pat. No. 3,939,806; U.S. Pat. No. 3,982,878, U.S. Pat. No. 4,167,919, U.S. Pat. No. 4,308,844; U.S. Pat. No. 4,440,545; U.S. Pat. No. 4,599,865; U.S. Pat. No. 4,841,731; U.S. Pat. No. 5,775,091, U.S. Pat. No. 5,293,857; U.S. Pat. No. 5,388,395; U.S. Pat. No. 5,782,081, U.S. Pat. No. 5,775,091; U.S. Pat. No. 5,899,072; U.S. Pat. No. 5,924,287; U.S. Pat. No. 6,212,876; U.S. Pat. No. 6,290,184; and U.S. Pat. No. 6,698,183. The closest work to this instant invention is U.S. Pat. No. 4,841,731 and U.S. Pat. No. 6,289,666 B 1. While each of these patents present improvements in combustion technology, each leaves issues that have left the commercialization of such a combustion engine impractical.
     Combustion Engine Thermodynamics—Much has been much done mechanically and chemically to combat the environmental issues associated with hydrocarbon combustion. Often, industrial facilities are outfitted with expensive scrubber systems whenever the politics demand installation and/or the business supports installation. As another example, the internal combustion engine has been enhanced significantly to make the engine more fuel efficient and environmentally friendly. However, even with enhancement, the internal combustion engine is only approximately 20 percent efficient and the gas turbine/steam turbine system is only approximately 20 to 40 percent efficient. The internal combustion engine looses as a percentage of available energy fuel value: 1) approximately 35 percent in the exhaust, 2) approximately 35 percent in cooling, 3) approximately 9 percent in friction, and 4) approximately 3 percent due to combustion performance, leaving the engine approximately less than 20 percent efficient.   

     An internal combustion engine produces power to perform work as a result of a complex series of interactions among “Billions and billions of molecules on a microscopic scale.” (quoting Carl Sagan) Thermodynamics is a branch of engineering, chemistry and physics that allows one to reduce this chaotic process to a relatively simple system based on the behavior of these molecules in the aggregate or, in other words, on a macroscopic scale. 
     For example, each molecule of a gas flies around with a speed that is a function of its particular temperature. Thermodynamics allows one to assign a single temperature to an entire volume of gas molecules based on the average temperature of all the molecules. Other macroscopic variables used to describe the behavior of a gas are the pressure within the enclosing container, the volume of the container and the number of molecules of gas present. The relationship between these variables can be approximated by the ideal gas law: 
       PV=nRT 
     where P, V and T are the absolute pressure, volume and absolute temperature, respectively. N (n) is the number of moles of gas (1 mole=6.023×10 23  molecules) and R is the universal gas constant (0.0821 liter-atmosphere/mole-K). 
     There are three basic laws of thermodynamics. The first, called the zeroth, law states that if object A is in thermal equilibrium with object B and object B is in thermal equilibrium with object C then object A and object C will also be in thermal equilibrium. This law is the basis of thermometry in which a thermometer can be used to compare the temperature of one object with another. 
     The next law, which is called the first law in the traditional numbering scheme, states that the change in the internal energy of a system is equal to the sum of the heat transferred from the system, the entropy transferred from the system and the amount of work done by the system. In other words, any thermal energy transferred into a system can be used to change the internal energy of that system (by changing its temperature) or to perform external work. This is a statement of the law of conservation of energy for thermal processes. 
     The final law, the second, essentially says that any heat engine cannot convert all of the energy put in to it to useful work. There will always be some waste heat left over. 
     A system&#39;s temperature is a measure of its internal energy. If heat is added to a volume of gas molecules and the system does not perform any external work the relationship between the heat added and the temperature can be described by: 
       Q=nC v ΔT or Q=nC p ΔT,
 
     wherein:  Q  is the amount of heat transferred, n is the number of moles of gas present, ΔT is the temperature change, and C v  as well as C p  are called the specific heat at constant volume and the specific heat at constant pressure, respectively, which depend on the type of gas. The first equation applies if the process takes place without a change in volume (a constant volume or isochoric process) and the second equation applies if the process takes places at constant pressure (a constant pressure or isobaric process). 
     The work done by a system can be found by multiplying the component of the force exerted in the direction of motion times the distance moved. For more complex systems where the force may not be constant the work can be calculated using calculus by integrating the following equation: 
       dW=Fdx, 
     wherein: dW is the increment of work, F is force and dx is the incremental distance moved. For a machine consisting of a piston in a closed cylinder the force exerted against the piston is given by the product of the pressure in the cylinder, P, and the area of the piston, A, e.g. 
       dW=PAdx. 
     Note that the term Adx is just the amount the volume of the closed cylinder changes when the piston moves a distance dx so the equation can be rewritten as: 
       dW=PdV. 
     In order to integrate this equation it is necessary to know the relationship between pressure and volume for the process. Such relationships can be displayed on a P-V diagram which is a plot with P as the vertical axis and V as the horizontal axis. There are a number of standard P-V processes illustrated on  FIG. 2 . The solid black line represents an isothermal expansion from 1 liter to 5 liters. The equation describing this curve is the ideal gas law: 
       PV=nRT, 
     wherein: P is the absolute pressure, V the volume, n is the number of moles of gas present, R is the universal gas constant and T is the absolute temperature. Isothermal means that the temperature is constant during the process. The work done by the system during the expansion can be calculated by integrating the work equation with the P replaced by a function of V from the governing ideal gas law: 
     
       
         
           
             W 
             = 
             
               
                 ∫ 
                 
                   P 
                    
                   
                      
                     V 
                   
                 
               
               = 
               
                 nRT 
                  
                 
                   
                     ∫ 
                     1 
                     5 
                   
                    
                   
                     
                       1 
                       V 
                     
                      
                     
                         
                     
                      
                     
                       
                          
                         V 
                       
                       . 
                     
                   
                 
               
             
           
         
       
     
     Notice that this integral represents the area on the P-V diagram that lies under the isothermal curve. 
     The gray curve represents an adiabatic expansion from 1 to 5 liters. Adiabatic means that no heat is transferred during the process. Notice that the adiabatic curve is steeper than the isothermal curve. The relationship between pressure and volume for an adiabatic curve is given by the following equation: 
       PVT y =constant 
     where, Υ is the ratio of specific heat at constant pressure to the specific heat at constant volume (C p /C v ) for the contained gas with a typical value of 1.4 for the types of gases involved in gasoline combustion engines. Generally, an isothermal process occurs slowly so heat can be transferred into or out of the system to maintain the constant temperature. An adiabatic process, by contrast, generally occurs rapidly so heat does not have a chance to flow. 
     The dotted black line describes an isobaric (constant pressure) process. The work done during this process is simply: 
         W=P ×( V   f   −V   i )
 
     The final dotted grey line represents an isochoric (constant volume) process. Since the area under this curve is zero no work is done. 
       FIG. 3  represents a cyclic process for a theoretical system called a Carnot engine. Path a to b is an isothermal compression at 400K. Path b to c is an adiabatic compression. Path c to d is an isothermal expansion at 600K and d back to a is an adiabatic expansion. The four paths define a closed path in P-V space. The enclosed area is the net work performed by the engine for each completed cycle around the clockwise path described. If the path had been in the counter clockwise direction the net work would have been negative. 
       FIG. 4  presents the Otto Cycle, which approximates the operation of a gasoline-powered internal combustion engine. Path a to b represents the intake stroke during which the air-fuel mixture is drawn into the cylinder as the piston moves outward. This process occurs at roughly atmospheric pressure (assuming a normally aspirated engine). Next, the intake valve closes and the piston moves inward compressing the mixture along the path from b to c. This is an adiabatic process since it happens fairly quickly. Work is done on the gas and its internal energy increases. 
     At the end of the compression stroke the mixture is ignited and the pressure increases rapidly along the path from c to d. This process happens very quickly and is essentially a nearly pure isochoric (constant volume) process. No work is done during this process so the heat of combustion goes entirely into raising the internal energy of the constituent gases. The power stroke is next and is an adiabatic expansion from d to e. During this process the system does external work and the internal energy decreases. At the end of the power stroke the exhaust valve is opened and the exhaust gases escape very quickly in what is essentially another isochoric process moving along path e to b. Finally, the piston again moves inward forcing out the remaining exhaust gases at atmospheric pressure along the path b to a. And the cycle repeats. . . . 
     The net work performed by the Otto Engine is given by the area enclosed by the four paths b to c to d to e to b. The work done during the intake and exhaust strokes (the areas under paths a to b and b to a) cancel each other.
     A Hypothetical Gasoline Engine—Let us consider the following hypothetical gasoline engine in order to put some actual numbers to the Otto cycle described previously. Let us have 6 cylinders with 100 mm bore and 78.9 mm stroke and a compression ration of 10; then:   

     1. Compression
         During the compression stroke:       

     
       
         
           
             
               Engine 
                
               
                   
               
                
               displacement 
             
             = 
             
               π 
               · 
               
                 
                   ( 
                   
                     bore 
                     2 
                   
                   ) 
                 
                 2 
               
               · 
               
                 ( 
                 stroke 
                 ) 
               
               · 
               
                 ( 
                 
                   # 
                    
                   
                       
                   
                    
                   of 
                    
                   
                       
                   
                    
                   
                     cyls 
                     . 
                   
                 
                 ) 
               
             
           
         
       
       
         
           
             
               
                 
                   
                     Displacement 
                      
                     
                         
                     
                      
                     per 
                      
                     
                         
                     
                      
                     cylinder 
                   
                   = 
                   
                     π 
                     · 
                     
                       
                         ( 
                         
                           50 
                            
                           
                               
                           
                            
                           mm 
                         
                         ) 
                       
                       2 
                     
                     · 
                     
                       ( 
                       
                         78.9 
                          
                         
                             
                         
                          
                         mm 
                       
                       ) 
                     
                   
                 
               
             
             
               
                 
                   = 
                   
                     620 
                      
                     
                         
                     
                      
                     
                       cm 
                       3 
                     
                      
                     
                         
                     
                      
                     
                       ( 
                       
                         0.62 
                          
                         
                             
                         
                          
                         l 
                       
                       ) 
                     
                   
                 
               
             
           
         
       
       
         
           
             
               Compression 
                
               
                   
               
                
               ratio 
             
             = 
             
               
                 c 
                 . 
                 r 
                 . 
               
               = 
               
                 
                   displacement 
                   + 
                   
                     dead 
                      
                     
                         
                     
                      
                     space 
                   
                 
                 
                   dead 
                    
                   
                       
                   
                    
                   space 
                 
               
             
           
         
       
         
         
           
             The dead space (volume remaining when the piston is fully inserted) can be calculated from the following equation: 
           
         
       
    
     
       
         
           
             
               c 
               . 
               r 
               . 
             
             = 
             
               10.0 
               = 
               
                 
                   
                     620 
                     + 
                     
                       d 
                       . 
                       s 
                       . 
                     
                   
                   
                     d 
                     . 
                     s 
                     . 
                   
                 
                 → 
                 
                   69 
                    
                   
                       
                   
                    
                   
                     mm 
                     3 
                   
                    
                   
                       
                   
                    
                   
                     ( 
                     
                       0.069 
                        
                       
                           
                       
                        
                       l 
                     
                     ) 
                   
                 
               
             
           
         
       
         
         
           
             For simplicity, 0.069 L≈0.070 L for the dead space. The number of moles of gas (air and gasoline vapor) in the cylinder at the beginning of the compression stroke from the ideal gas law. 
           
         
       
    
     
       
         
           
             n 
             = 
             
               
                 P 
                 · 
                 V 
               
               
                 n 
                 · 
                 R 
               
             
           
         
       
       
         
           
             n 
             = 
             
               
                 
                   
                     ( 
                     
                       1.0 
                        
                       
                           
                       
                        
                       atm 
                     
                     ) 
                   
                   · 
                   
                     ( 
                     
                       0.69 
                        
                       
                           
                       
                        
                       l 
                     
                     ) 
                   
                 
                 
                   
                     ( 
                     
                       
                         0.0821 
                          
                         
                             
                         
                          
                         l 
                       
                       - 
                       
                         atm 
                         / 
                         mole 
                       
                       - 
                       K 
                     
                     ) 
                   
                   · 
                   
                     ( 
                     
                       300 
                        
                       
                           
                       
                        
                       K 
                     
                     ) 
                   
                 
               
               = 
               
                 0.0280 
                  
                 
                     
                 
                  
                 moles 
               
             
           
         
       
         
         
           
             The pressure in the cylinder at the end of the compression stroke (P, V) can be calculated from the pressure and volume at the beginning of the compression stroke (P 0 , V 0 ) as follows: 
           
         
       
    
     
       
         
           
             
               P 
               · 
               
                 V 
                 γ 
               
             
             = 
             
               constant 
               = 
               
                 
                   P 
                   0 
                 
                 · 
                 
                   V 
                   0 
                   γ 
                 
               
             
           
         
       
       
         
           
             P 
             = 
             
               
                 P 
                 0 
               
               · 
               
                 
                   ( 
                   
                     
                       V 
                       0 
                     
                     V 
                   
                   ) 
                 
                 γ 
               
             
           
         
       
       
         
           
             P 
             = 
             
               
                 
                   ( 
                   
                     1.0 
                      
                     
                         
                     
                      
                     atm 
                   
                   ) 
                 
                 · 
                 
                   
                     ( 
                     
                       
                         0.690 
                          
                         
                             
                         
                          
                         l 
                       
                       
                         0.070 
                          
                         
                             
                         
                          
                         l 
                       
                     
                     ) 
                   
                   1.4 
                 
               
               = 
               
                 24.6 
                  
                 
                     
                 
                  
                 atm 
               
             
           
         
       
         
         
           
             The temperature after compression is given by the ideal gas law: 
           
         
       
    
     
       
         
           
             T 
             = 
             
               
                 PV 
                 nR 
               
               = 
               
                 
                   
                     
                       ( 
                       
                         24.6 
                          
                         
                             
                         
                          
                         atm 
                       
                       ) 
                     
                     · 
                     
                       ( 
                       
                         0.070 
                          
                         
                             
                         
                          
                         l 
                       
                       ) 
                     
                   
                   
                     
                       ( 
                       
                         0.028 
                          
                         
                             
                         
                          
                         moles 
                       
                       ) 
                     
                     · 
                     
                       ( 
                       
                         0.0821 
                          
                         
                             
                         
                          
                         
                           l 
                           · 
                           
                             atm 
                             / 
                             mole 
                           
                           · 
                           K 
                         
                       
                       ) 
                     
                   
                 
                 = 
                 
                   749 
                    
                   
                       
                   
                    
                   K 
                 
               
             
           
         
       
         
         
           
             The resulting curve is shown in  FIG. 5 . 
           
         
       
    
     2. Combustion
         The chemical reaction between gasoline and air can be simplified as follows:       

       C 8 H 18 +12.5O 2 →8CO 2 +9H 2 O+1300 kcal (5443 kJ)
         Just prior to combustion there are 0.0280 moles of gas present in the cylinder. This gas is a mixture of gasoline vapor, O 2  and N 2 . The O 2  and N 2  came from air which is approximately 21% O 2  and 79% N 2 . The ratio of gasoline vapor to O 2  is given in the above equation. So a single equation can relate the relative amounts of all three gases present. If x represents the number of moles of air in the cylinder, then:       

     
       
         
           
             
               moles 
                
               
                   
               
                
               of 
                
               
                   
               
                
               
                 N 
                 2 
               
             
             = 
             
               0.79 
               · 
               x 
             
           
         
       
       
         
           
             
               moles 
                
               
                   
               
                
               of 
                
               
                   
               
                
               
                 O 
                 2 
               
             
             = 
             
               0.21 
               · 
               x 
             
           
         
       
       
         
           
             
               moles 
                
               
                   
               
                
               of 
                
               
                   
               
                
               
                 C 
                 8 
               
                
               
                 H 
                 18 
               
             
             = 
             
               
                 1 
                 12.5 
               
               · 
               0.21 
               · 
               x 
             
           
         
       
         
         
           
             The total number of moles is 0.0280 so x can be determined from the following equation: 
           
         
       
    
     
       
         
           
             
               
                 
                   1 
                   12.5 
                 
                 · 
                 
                   ( 
                   0.21 
                   ) 
                 
                 · 
                 x 
               
               + 
               
                 
                   ( 
                   0.21 
                   ) 
                 
                 · 
                 x 
               
               + 
               
                 
                   ( 
                   0.79 
                   ) 
                 
                 · 
                 x 
               
             
             = 
             
               0.0280 
                
               
                   
               
                
               moles 
             
           
         
       
         
         
           
             The result is 0.0275 moles of air. Inserting this value of x in the previous series of equations yields: 0.0005 moles of C 8 H 18 , 0.0058 moles of O 2  and 0.0218 moles of N 2 . From the chemical equation describing the combustion of gasoline and the number of moles of reactants we can calculate the number of moles of each of the reaction products. Each 12.5 moles of O 2  produces 8 moles of CO 2  and 9 moles of H 2 O. 
           
         
       
    
     
       
         
           
             
               
                 ( 
                 
                   0.0058 
                    
                   
                       
                   
                    
                   moles 
                    
                   
                       
                   
                    
                   
                     O 
                     2 
                   
                 
                 ) 
               
               · 
               
                 
                   8 
                    
                   
                       
                   
                    
                   moles 
                    
                   
                       
                   
                    
                   
                     CO 
                     2 
                   
                 
                 
                   12.5 
                    
                   
                       
                   
                    
                   moles 
                    
                   
                       
                   
                    
                   
                     O 
                     2 
                   
                 
               
             
             = 
             
               
                 0.0037 
                  
                 
                     
                 
                  
                 moles 
                  
                 
                     
                 
                  
                 
                   
                     
                       CO 
                       2 
                     
                      
                     
                       
 
                     
                     ( 
                     
                       0.0058 
                        
                       
                           
                       
                        
                       moles 
                        
                       
                           
                       
                        
                       
                         O 
                         2 
                       
                     
                     ) 
                   
                   · 
                   
                     
                       9 
                        
                       
                           
                       
                        
                       moles 
                        
                       
                           
                       
                        
                       
                         H 
                         2 
                       
                        
                       O 
                     
                     
                       12.5 
                        
                       
                           
                       
                        
                       moles 
                        
                       
                           
                       
                        
                       
                         O 
                         2 
                       
                     
                   
                 
               
               = 
               
                 0.0042 
                  
                 
                     
                 
                  
                 moles 
                  
                 
                     
                 
                  
                 
                   H 
                   2 
                 
                  
                 O 
               
             
           
         
       
         
         
           
             Since one mole of gasoline reacting with O 2  yields 5443 kJ, the above reaction of 0.0005 moles will yield 2.5 kJ of energy. No work is done during this process so the first law of thermodynamics requires this energy to be stored as internal energy of the reaction products which will raise their temperatures in proportion to the number of moles present and the specific heats of each gas. The heat capacities (in this case the molar-specific heats at constant volume) and number of moles (from the above formula) are as follows: 
           
         
       
    
     
       
         
           
               
               
               
               
               
             
               
                   
                   
               
               
                   
                 Gas 
                 Number of Moles 
                 Heat Capacity 
                 Units 
               
               
                   
                   
               
             
            
               
                   
                 N 2   
                 0.0218 
                 25.8 
                 J/mole-K 
               
               
                   
                 CO 2   
                 0.0037 
                 40.8 
                 J/mole-K 
               
               
                   
                 H 2 O 
                 0.0042 
                 37.0 
                 J/mole-K 
               
               
                   
                   
               
            
           
         
       
         
         
           
             The temperature rise can then be calculated using the following equation: 
           
         
       
    
     
       
      
       Q=n 
       N 
       
         2 
       
       ·C 
       V,N 
       
         2 
       
       ·ΔT+n 
       CO 
       
         2 
       
       ·C 
       V,CO 
       
         2 
       
       ·ΔT+n 
       H 
       
         2 
       
       O 
       ·C 
       V,H 
       
         2 
       
       O 
       ·ΔT  
      
         
         
           
             Rearranging the equation to solve for ΔT and inserting appropriate values: 
           
         
       
    
     
       
         
           
             
               Δ 
                
               
                   
               
                
               T 
             
             = 
             
               Q 
               
                 ( 
                 
                   
                     
                       n 
                       
                         N 
                         2 
                       
                     
                     · 
                     
                       C 
                       
                         V 
                         , 
                         
                           N 
                           2 
                         
                       
                     
                   
                   + 
                   
                     
                       n 
                       
                         CO 
                         2 
                       
                     
                     · 
                     
                       C 
                       
                         V 
                         , 
                         
                           CO 
                           2 
                         
                       
                     
                   
                   + 
                   
                     
                       n 
                       
                         
                           H 
                           2 
                         
                          
                         O 
                       
                     
                     · 
                     
                       C 
                       
                         V 
                         , 
                         
                           
                             H 
                             2 
                           
                            
                           O 
                         
                       
                     
                   
                 
                 ) 
               
             
           
         
       
       
         
           
             
               
                 
                   
                     Δ 
                      
                     
                         
                     
                      
                     T 
                   
                   = 
                   
                     
                       2.5 
                        
                       
                           
                       
                        
                       kJ 
                     
                     
                       ( 
                       
                         
                           0.02176 
                           · 
                           25.8 
                         
                         + 
                         
                           0.00368 
                           · 
                           40.8 
                         
                         + 
                         
                           0.00414 
                           · 
                           37.0 
                         
                       
                       ) 
                     
                   
                 
               
             
             
               
                 
                   = 
                   
                     2891 
                      
                     
                         
                     
                      
                     K 
                   
                 
               
             
           
         
       
       
         
           
             T 
             = 
             
               
                 
                   749 
                    
                   
                       
                   
                    
                   K 
                 
                 + 
                 
                   2891 
                    
                   
                       
                   
                    
                   K 
                 
               
               = 
               
                 3640 
                  
                 
                     
                 
                  
                 K 
               
             
           
         
       
         
         
           
             The pressure at the end of combustion can be calculated using the ideal gas law: 
           
         
       
    
     
       
         
           
             Pressure 
             = 
             
               
                 n 
                 · 
                 R 
                 · 
                 T 
               
               V 
             
           
         
       
       
         
           
             
               
                 
                   Pressure 
                   = 
                   
                     
                       
                         ( 
                         
                           0.02958 
                            
                           
                               
                           
                            
                           moles 
                         
                         ) 
                       
                       · 
                       
                         ( 
                         
                           
                             0.0821 
                              
                             
                                 
                             
                              
                             l 
                           
                           - 
                           
                             atm 
                             / 
                             mole 
                           
                           - 
                           K 
                         
                         ) 
                       
                       · 
                       
                         ( 
                         
                           3640 
                            
                           
                               
                           
                            
                           K 
                         
                         ) 
                       
                     
                     
                       0.070 
                        
                       
                           
                       
                        
                       l 
                     
                   
                 
               
             
             
               
                 
                   = 
                   
                     126.3 
                      
                     
                         
                     
                      
                     atm 
                      
                     
                         
                     
                      
                     
                       ( 
                       
                         1856 
                          
                         
                             
                         
                          
                         psi 
                       
                       ) 
                     
                   
                 
               
             
           
         
       
         
         
           
             The increase in pressure from 24.6 atm to 126.3 atm, at Cv, is plotted in  FIG. 5 . 
           
         
       
    
     3. Expansion 
     Having computed the pressure at the beginning of the expansion stroke (and knowing the volume) it is possible to calculate the pressure as a function of volume during the adiabatic expansion: 
     
       
         
           
             P 
             = 
             
               
                 P 
                 0 
               
               · 
               
                 
                   ( 
                   
                     
                       V 
                       o 
                     
                     V 
                   
                   ) 
                 
                 γ 
               
             
           
         
       
       
         
           
             P 
             = 
             
               
                 ( 
                 
                   126.3 
                    
                   
                       
                   
                    
                   atm 
                 
                 ) 
               
               · 
               
                 
                   ( 
                   
                     
                       0.070 
                        
                       
                           
                       
                        
                       l 
                     
                     V 
                   
                   ) 
                 
                 1.4 
               
             
           
         
       
     
     This line is plotted in the grey line on the P-V diagram. 
     4. Exhaust 
     The exhaust stroke is plotted in  FIG. 5 . 
     5. Work Performed
         Work is only done by (or on) the system during the adiabatic processes (when the piston is actually moving) which can be calculated as follows:       

     
       
         
           
             W 
             = 
             
               ∫ 
               
                 P 
                 · 
                 
                    
                   V 
                 
               
             
           
         
       
       
         
           
             
               P 
               · 
               
                 V 
                 γ 
               
             
             = 
             
               
                 P 
                 0 
               
               · 
               
                 V 
                 o 
                 γ 
               
             
           
         
       
       
         
           
             W 
             = 
             
               ∫ 
               
                 
                   
                     
                       P 
                       0 
                     
                      
                     
                       ( 
                       
                         
                           V 
                           0 
                         
                         V 
                       
                       ) 
                     
                   
                   γ 
                 
                 · 
                 
                    
                   V 
                 
               
             
           
         
       
       
         
           
             W 
             = 
             
               
                 
                   
                     
                       P 
                       0 
                     
                     · 
                     V 
                   
                   
                     1 
                     - 
                     γ 
                   
                 
                  
                 
                   
                     ( 
                     
                       
                         V 
                         0 
                       
                       V 
                     
                     ) 
                   
                   γ 
                 
               
                
               
                  
                 
                   V 
                   1 
                 
                 
                   V 
                   f 
                 
               
             
           
         
       
         
         
           
             Values for evaluating this integral are: 
           
         
       
    
     
       
         
           
               
               
               
               
               
             
               
                   
                   
               
               
                   
                 Parameter 
                 Compression 
                 Expansion 
                 Units 
               
               
                   
                   
               
             
            
               
                   
               
            
           
           
               
               
               
               
               
            
               
                   
                 P 0   
                 1.0 
                 126.3 
                 atm 1   
               
               
                   
                 V 0  (V i ) 
                 0.690 
                 0.070 
                 L 2   
               
               
                   
                 Vf 
                 0.070 
                 0.690 
                 L 
               
               
                   
                 Work 
                 −2.58 
                 13.25 
                 L-atm 
               
               
                   
                   
               
               
                   
                   1 atm = atmosphere of pressure; 
               
               
                   
                   2 L = Liter of volume 
               
            
           
         
       
         
         
           
             The work done during the expansion is 13.25 L-atm and the work done during the compression is −2.58 L-atm. The net work performed during each cycle is 10.67 L-atm (1.08 kJ). 
           
         
       
    
     6. Total horsepower
         For a typical automobile traveling at 60 MPH the engine speed is approximately 3000 rpm or 50 revolutions per second. Since a four stroke cylinder has a power stroke only every other revolution it will be firing at a rate of 25 power strokes per second. A six-cylinder engine will have 150 power strokes per second. Thus, the total power will be:       

       (150 power strokes/sec)·(1.08 kJ/stroke)/0.746 kW/hp=217 hp
         However, there are a whole host of effects that take this energy away such as friction, inefficient combustion, heat losses, entropy losses and accelerating inertial masses. This can easily take up 80 to 85% of the power leaving only about 35 to 45 hp delivered to the rear wheels (at 60 MPH).       Liquefaction—Liquefaction incorporates cryogenic refrigeration, wherein there are many known methods of cryogenic refrigeration. A good reference of cryogenic refrigeration methods and processes known in the art would be “Cryogenic Engineering,” written by Thomas M. Flynn and printed by Dekker. As written by Flynn, “cryogenic refrigeration and liquefaction are the same processes, except liquefaction takes off a portion of the refrigerated liquid which must be made up, wherein refrigeration all of the liquid is recycled. All of the methods and processes of refrigeration and liquefaction are based upon the same basic refrigeration principals, as depicted in Flow Diagram 1.   

     As written by Flynn, there are many ways to combine the few components of work (compression), rejecting heat, expansion and absorbing heat. There exist in the art many methods and processes of cryogenic refrigeration, all of which can be adapted for cryogenic liquefaction. A listing of those refrigeration cycles would include: Joule Thompson, Sterling, Brayton, Claude, Linde, Hampson, Posde, Ericsson, Gifford-McMahon and Vuilleumier. As written by Flynn, “There are as many ways to combine these few components as there are engineers to combine them.” (It is important to note, as is known in the art, that H 2  has a negative Joule-Thompson coefficient until temperatures of approximately 350 R or less are obtained.) 

 
     While it is well known in the chemical industry that the cryogenic distillation of air into O 2 , N 2  and Ar 2 ; cryogenic distillation is the most economical pathway to produce these elemental diatomic gases. Previous work performed to separate air into its components is herein referenced in U.S. Pat. No. 4,112,875; U.S. Pat. No. 5,245,832; U.S. Pat. No. 5,976,273; U.S. Pat. No. 6,048,509; U.S. Pat. 6,082,136; U.S. Pat. No. 6,298,668 and U.S. Pat. No. 6,333,445.
     Steam Conversion—The discovered instant invention relates to producing H 2  from steam, since steam is the physical state of the H 2 O product from combustion. Previous work in this field has focused on refinery or power plant exhaust gases; none of that work discusses the separation of steam back into H 2 . Previous work performed to utilize the products of hydrocarbon combustion from an internal combustion engine can be referenced in U.S. Pat. No. 4,003,343. Previous work in corrosion is in the direction of preventing corrosion instead of encouraging corrosion, yet is herein referenced in U.S. Pat. No. 6,315,876, U.S. Pat. No. 6,320,395, U.S. Pat. No. 6,331,243, U.S. Pat. No. 6,346,188, U.S. Pat. No. 6,348,143 and U.S. Pat. No. 6,358,397.   Electrolysis—The discovered instant invention relates to electro-chemically converting H 2 O into O 2  and H 2 . While there have been improvements in the technology of electrolysis and there have been many attempts to incorporate electrolysis with a combustion engine, wherein the hydrocarbon fuel is supplemented by H 2  produced by electrolysis, there has been no work with electrolysis to fuel a combustion engine wherein electrolysis is a significant source of O 2  and H 2 . Previous work in electrolysis as electrolysis relate to combustion systems is herein referenced in U.S. Pat. No. 6,336,430, U.S. Pat. No. 6,338,786, U.S. Pat. No. 6,361,893, U.S. Pat. No. 6,365,026, U.S. Pat. No. 20 6,635,032 and U.S. Pat. No. 4,003,035.   Electricity—The discovered instant invention relates to the production of electricity. The mechanical energy to turn a generator (again, a generator means a generator, alternator or dynamo) is produced by the instant invention. This is while the steam energy for a steam driven generator may be produced by the instant invention; instant invention exhaust steam energy may drive a steam turbine, thereby turning a generator to create an electrical current.   

     The discovered instant invention presents a combustion turbine, wherein the exhaust gas is at least primarily if not totally H 2 O. While there has been much work in the design of steam turbines, in all cases steam for the steam turbine is generated by heat transfer, wherein said heat for heat transfer is created by nuclear fission or hydrocarbon combustion. Previous work in steam turbine generation technology and exhaust turbine technology is herein referenced in: U.S. Pat. No. 6,100,600, U.S. Pat. No. 6,305,901, U.S. Pat. No. 6,332,754. U.S. Pat. No. 6,341,941, U.S. Pat. No. 6,345,952, U.S. Pat. No. 4,003,035, U.S. Pat. No. 6,298,651, U.S. Pat. No. 6,354,798, U.S. Pat. No. 6,357,235, U.S. Pat. No. 6,358,004 and U.S. Pat. No. 6,363,710, the closest being U.S. Pat. No. 4,094,148 and U.S. Pat. No. 6,286,315 B1. 
     The discovered instant invention relates to photovoltaic means to create electricity, wherein said electricity is used in electrolysis to create at least one of H 2  and O 2  from H 2 O, and wherein said H 2  and/or said O 2  is used as a fuel in said instant invention. There are many means of photovoltaics, as is known in the art. There are many means wherein a photovoltaic cell may be used to create electricity for the electrolytic separation of H 2 O into H 2  and O 2 . Previous work in photovoltaic cells in relation to the production of H 2  is herein referenced in: U.S. Pat. No. 5,797,997, U.S. Pat. No. 5,900,330, U.S. Pat. No. 5,986,206, U.S. Pat. No. 6,075,203, U.S. Pat. No. 6,128,903, U.S. Pat. No. 6,166,397, U.S. Pat. No. 6,172,296, U.S. Pat. No. 6,211,643, U.S. Pat. No. 6,214,636, U.S. Pat. No. 6,279,321, U.S. Pat. No. 6,372,978, U.S. Pat. No. 6,459,231, U.S. Pat. No. 6,471,834, U.S. Pat. No. 6,489, 553, U.S. Pat. No. 256,503,648, U.S. Pat. No. 6,508,929, U.S. Pat. No. 6,515,219 and U.S. Pat. No. 6,515,283.
     H 2 O Treatment Chemistry—The discovered instant invention relates to methods of controlling corrosion, scale and deposition in H 2 O applications. U.S. Pat. No. 4,209,398 issued to Ii, et al., on Jun. 24, 1980, referenced herein, presents a process for treating H 2 O to inhibit formation of scale and deposits on surfaces in contact with the H 2 O and to minimize corrosion of the surfaces. The Ii, et al. process comprises mixing in the H 2 O an effective amount of H 2 O soluble polymer containing a structural unit that is derived from a monomer having an ethylenically unsaturated bond and having one or more carboxyl radicals, al least a part of said carboxyl radicals being modified, and one or more corrosion inhibitor compounds selected from the group consisting of inorganic phosphoric acids and H 2 O soluble salts therefore. Phosphonic acids and H 2 O soluble salts thereof, organic phosphoric acids and H 2 O soluble salts thereof, organic phosphoric acid esters and H 2 O—soluble salts thereof and polyvalent metal salts, capable of being dissociated to polyvalent metal ions in H 2 O.   

     U.S. Pat. No. 4,442,009 issued to O&#39;Leary, et al., on Apr. 10, 1984, referenced herein, presents a method for controlling scale formed from H 2 O soluble calcium, magnesium and iron impurities contained in boiler H 2 O. The method comprises adding to the H 2 O a chelant and H 2 O soluble salts thereof, a H 2 O soluble phosphate salt and a H 2 O soluble poly methacrylic acid or H 2 O soluble salt thereof. 
     U.S. Pat. No. 4,631,131 issued to Cuisia, et al., on Dec. 23, 1986, referenced herein, presents a method for inhibiting formation of scale in an aqueous steam generating boiler system. Said method comprises a chemical treatment consisting essentially of adding to the H 2 O in the boiler system scale-inhibiting amounts of a composition comprising a copolymer of maleic acid and alkyl sulfonic acid or a H 2 O soluble salt thereof; hydroxyl ethylidene, 1-diphosphic acid or a H 2 O soluble salt thereof and a H 2 O soluble sodium phosphate hardness precipitating agent. 
     U.S. Pat. No. 4,640,793 issued to Persinski, et al., on Feb. 3, 1987, referenced herein, presents an admixture, and its use in inhibiting scale and corrosion in aqueous systems, comprising: (a) a H 2 O soluble polymer having a weight average molecular weight of less than 25,000 comprising an unsaturated carboxylic acid and an unsaturated sulfonic acid, or their salts, having a ratio of 1:20 to 20:1, and (b) at least one compound selected from the group consisting of H 2 O soluble polycarboxylates, phosphonates, phosphates, polyphosphates, metal salts and sulfonates. The Persinski patent presents chemical combinations which prevent scale and corrosion. 
     The instant invention relates to methods of storing hydrogen; as hydrogen is a preferred fuel in applications beyond the surface of the Earth, herein after referred to as Space Applications. Hydrogen is preferred as compared to a hydrocarbon in Space Applications; as, hydrogen has near 3 times the available combustion energy per pound as compared to any hydrocarbon; this is while all hydrocarbons have a freezing point which is much higher than hydrogen, and while the temperature in most Space Applications is near 5 to 250 K. As an example, the lightest hydrocarbon, methane, which has the lowest freezing point of any hydrocarbon has a freezing point of 91 K (1 atm), which is in stark contrast to hydrogen, which has a freezing point of 3 K (1 atm). This is while hydrogen has a significant vapor pressure, even at 5 K. 
     Applicant attended the NASA Exploration Systems Mission Directorate (ESMD) Technology Exchange Conference in Galveston, Tex. on Nov. 14-15, 2007, wherein hydrogen boil-off and required fuel cell cleanliness in a dust environment were presented as significant challenges to future space flight to the Moon and Mars, e.g. Project Constellation. It was presented by NASA that the Apollo Program after launch lost near 6-10 percent of stored H 2  in a matter of days; said loss was due to H 2  vapor pressure, e.g. H 2  boil-off; this is while lift-off costs are in the range of $10,000 to $25,000 per pound. As of the filing of the instant invention, Applicant is efforting work with propulsion and cryogenic storage engineers at NASA to further application of the instant invention in Constellation. 
     SUMMARY OF THE INVENTION 
     A primary object of the invention is to devise effective, efficient and economically feasible combustion methods, processes, systems and apparatus in Space Applications, wherein engine power, effectiveness and efficiency are improved. 
     Another object of the invention is to devise effective, efficient and economically feasible combustion means in Space Applications for an internal combustion engine. 
     Another object still of the invention is to devise effective, efficient and economically feasible combustion means in Space Applications for a turbine combustion engine. 
     Still another object of the invention is to devise effective, efficient and economically feasible combustion means in Space Applications for electrical energy generation. 
     Further, another object of the invention is to devise effective, efficient and economically feasible means of fuel and oxidizer storage in Space Applications. 
     Still further yet, another object of the invention is to devise effective, efficient and economically feasible combustion means in Space Applications that include H 2  and O 2 , wherein the temperature of combustion is controlled so that economical materials of construction for a combustion engine can be used. 
     Still further yet also, another object of the invention is to devise effective, efficient and economically feasible combustion means in Space Applications that include H 2  and O 2 , wherein the temperature of combustion is not controlled with a water jacket cooling system. 
     Additional objects and advantages of the invention will be set forth in part in a description which follows and in part will be obvious from the description, or may be learned by practice of the invention. 
     The instant invention manages energy much more efficiently than the traditional combustion engine, which operates with hydrocarbons and air. This is especially the case with respect to the internal combustion engine (ICE). ICE, generally, looses approximately 60 to 85 percent of available combustion energy in: heat losses from the engine, engine exhaust gases and unused mechanical energy. In contrast, the instant invention recaptures significant energy losses by converting lost energy (enthalpy, entropy and mechanical energy) into potential energy and internal energy. The instant invention generates additional power by utilizing the power of steam to increase engine efficiency while using H 2 O and the release of said steam to cool the engine. It is further discovered that this instant invention provides the thermodynamic capability to improve combustion efficiency while providing improved engine performance, wherein said improved engine performance relates to both the produced engine power and the available power produced per cubic inch of engine displacement. 
     The discovered instant invention utilizes the energy of combustion of H 2  fuel with O 2  as the oxidizer. The combustion of H 2  with O 2  provides a combustion envelope having attributes which are somewhat different than those for any hydrocarbon. In comparison and contrast, the auto-ignition (combustion without a spark) temperature of H 2  is 585° C., while that of methane and propane is 540 and 487° C., respectively. The combustion envelope, by volume, for H 2  in air is near 4-75% (air is near 20% O 2 ), while that of methane and propane is near 5.3-15% and 2.1-9.5%, respectively. The explosive regions for H 2  and methane are 13-59% and 6.3-14%, respectively. It has, therefore, been discovered in the instant invention that H 2  provides a combustion envelope which allows for a cooling of combustion and of combustion exhaust gases in the combustion chamber, wherein said combustion envelope is not available with a hydrocarbon. 
     The combustion product of H 2  and O 2  is H 2 O. This combustion reaction is somewhat similar to that of hydrocarbon combustion; however, carbon and nitrogen (from air) are removed from the reaction. The combustion of H 2  with O 2  produces H 2 O, which is in stark contrast to the combustion of fossil fuels which produce in addition to H 2 O oxides of carbon (CO X ) oxides of N 2  (NO X ) and whenever the hydrocarbon is contaminated with S, oxides of sulfur (SO X ). 
     The discovered instant invention uses the first and second laws of thermodynamics as an asset. In contrast, hydrocarbon combustion technologies have the first and second laws of thermodynamics as a liability. Specifically: 
       Combustion Energy=Available Work+Combustion Losses Friction Energy Losses+Enthalpy Losses+Entropy Losses+Potential Energy, 
     which can be rewritten as: 
       Combustion Energy=Available Work+Combustion Losses+Friction Energy Losses+Heat and Cooling losses+Exhaust losses+Potential Energy, 
     And, in the case of most hydrocarbon combustion systems: 
       Combustion Energy=(15-20%)+(1-5%)+(5-15%)+≈35%+≈35%+0,
 
     leaving only about 15 to 20% of combustion energy available for work. 
     In comparison and contrast the discovered instant invention preferably operates with an insulated combustion chamber or engine block and a recycling of exhaust gas energy, thereby redefining the thermodynamics of combustion to be approximated by: 
       Combustion Energy (100%)=Available Work+Friction Energy Losses+Recycled Energy Losses+Potential Energy 
     Therefore, 100%=(15 to 20%)+(1-5%)+(5-15%)+(5-40%)+Poteential Energy. And, Potential Energy=25-75% excluding recycle losses, thereby producing a final engine efficiency of approximately 40 to 90% by incorporating the available potential energy of recycle. A preferred energy flow diagram for the instant invention is depicted in  FIG. 6 . 
     The instant invention preferably adds H 2 O to the combustion chamber, preferably as low steam, at least once during at least one cycle to cool the engine, thereby creating higher pressure steam, and thereby further powering the engine. It is a preferred embodiment of the instant invention within an internal combustion engine to have at least one cycle wherein no fuel (H 2 ) or oxidizer (O 2 ) is added to the combustion chamber, wherein H 2 O, preferably as steam, is added, wherein the heat of the combustion chamber is transferred into said H 2 O thereby cooling said combustion chamber and providing power due to the steam energy created by said heat transfer to said H 2 O. It is a preferred embodiment of the instant invention within a turbine to add H 2 O as either a low pressure gas (steam) or as a liquid (H 2 O) to at least one of the combustion chamber and the steam turbine, wherein the heat of at least one of the combustion chamber and the combustion product (steam) is transferred into said H 2 O thereby cooling said combustion chamber and providing power due to the steam energy created by said heat transfer. The capability of the instant invention to provide further power and cooling by the addition of H 2 O in at least one cycle other than the combustion cycle in an internal combustion engine or to provide further power and cooling by the addition of H 2 O to at least one location in a turbine is herein defined as “Energy Recovery Cooling”. 
     Further, instant invention power capability is enhanced by the discovered capability of the instant invention to provide at least one of fuel (O 2 ) and of oxidizer (O 2 ) to combustion under pressure. This discovered capability of the instant invention provides a significant power capability which is not practical in a hydrocarbon air induction combustion system. Specifically, a hydrocarbon air induction combustion system must increase rpm to increase power; as, the combustion chemistry within each revolution is limited by the availability of oxidizer, O 2 , in air at atmospheric pressure. In contrast, the discovered instant invention can provide O 2 , as well as H 2 , to combustion under pressure. 
     The discovered instant invention in a preferred embodiment stores H 2  in a cryogenic state, wherein said cryogenic capability is preferably provided by a liquefaction means powered by an engine of the instant invention. It is it most preferred to store said cryogenic H 2  below its Joule Thompson Curve, thereby causing said H 2  to have a positive Joule Thompson coefficient (JtC) in order to provide further chilling and/or liquefaction of said H 2 . While significantly improving the storage energy per unit volume, chilled or liquefied, H 2  provides a discovered capability to provide H 2  to combustion under pressure. As the discovered instant invention is preferred to provide to combustion under pressure at least one of H 2  and of O 2 , the discovered instant invention presents an engine which can increase power or available work about independent of rpm, as well as increase power or work directly dependant upon rpm. This discovered capability of the instant invention presents an engine which has a torque curve which is at least partially independent of rpm, or on a diagram of torque vs. rpm, the capability of a vertical or near vertical torque curve or the capability of a torque curve wherein at least one portion of the torque curve is about vertical, e.g. vertical torque curve. 
     Further yet still, the discovered instant invention in yet another embodiment improves the previously known Otto cycle by the addition of H 2 O, preferably as steam, to the combustion chamber during exhaust, thereby cooling the engine during exhaust prior to the next cycle. This addition of water during exhaust has the instant invention the capability of increasing available work, P×V. 
     Further still yet, as the discovered instant invention in still yet another preferred embodiment can operate “in diesel fashion” due to the auto-ignition temperature of H 2 , which is near 585° C.; the discovered instant invention has the capability to further manage the cycle by the addition of either H 2  (fuel) or O 2  (oxidizer) during combustion. This discovered capability of the instant invention provides the ability of “a slow burn” during the power or expansion portion of the cycle. This slow burn capability of the instant invention is herein termed the “Newsom burn”. 
     And further still yet, as the discovered instant invention has the capability of managing engine power by H 2 O addition to cool the engine during the exhaust stroke and/or a cooling cycle, as well as the capability of providing at least one of H 2  and O 2  to combustion during power generation (in the case of an ICE, this would be the power stroke and in the case of a turbine this would be anytime during the combustion of fuel); therefore, the discovered instant invention has the capability of significantly managing and/or manipulating the work (P-V) curves of an engine such that instant invention can manipulate the net work output for each engine cycle relative to conventional internal combustion engines which operate from the Otto Cycle. This capability of managing engine power is depicted in  FIGS. 7 and 8 , wherein  FIG. 7  depicts the preferred embodiment of a two cycle version and  FIG. 8  depicts a preferred embodiment of a four cycle version; this instant invention variant to the Otto cycle incorporating at least one of: H 2 O cooling during exhaust, H 2 O cooling during at least one additional cycle and diesel like “slow burn” during power is defined in the instant invention defines a new combustion cycle termed the “Haase Cycle”. 
     Finally, the instant invention has been discovered to provide means of liquefaction for H 2  and/or O 2  storage. In Space Applications, it is of high importance to maintain H 2  fuel mass; this is when H 2  fuel and O 2  oxidizer have significant vapor pressure. As depicted in  FIG. 18 , the instant invention provides means, e.g. method, system process and apparatus, to control H 2  fuel mass storage by means of liquefaction of H 2  vapor from H 2  fuel storage using available H 2  fuel and available O 2  oxidizer to power an engine of the instant invention, wherein said engine powers at least one compressor for liquefaction of at least one of H 2  fuel and/or O 2  oxidizer. 
    
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
       A better understanding of the present invention can be obtained when the following descriptions of the preferred embodiments are considered in conjunction with the following drawings, in which: 
         FIG. 1  illustrates a legend for  FIGS. 2 through 20 . 
         FIG. 2  illustrates a graphical representation of various thermodynamic processes as functions of pressure and volume 
         FIG. 3  illustrates a graphical representation of the work, pressure-volume, diagram of a Carnot Cycle. 
         FIG. 4  illustrates a graphical representation of the work, pressure-volume, diagram for an Otto Cycle. 
         FIG. 5  illustrates a graphical representation of the work, pressure-volume, diagram for an Atypical Gasoline Engine. 
         FIG. 6  illustrates in block diagram form the preferred embodiment of the instant invention as the instant invention applies to ICE. 
         FIG. 7  illustrates a graphical representation of the work, pressure-volume, diagram for a 2 cycle variant of the Haase Cycle. 
         FIG. 8  illustrates a graphical representation of the work, pressure-volume, diagram for a 4 cycle variant of the Haase Cycle. 
         FIG. 9  illustrates a graphical representation of the work, pressure-volume, diagram for a 4 cycle variant of the instant invention. 
         FIG. 10  presents a computer result of a Model, wherein T 0 =100 K, the moles of H 2 O range from 0.084 to 0.2521 and the moles of H 2  range from 0.005 to 0.016. 
         FIG. 11  presents a computer result of said Model, wherein T 0 =200 K, the moles of H 2 O range from 0.042 to 0.126 and the moles of H 2  range from 0.005 to 0.016. 
         FIG. 12  presents a computer result of said Model, wherein T 0 =300 K, the moles of H 2 O range from 0.028 to 0.084 and the moles of H 2  range from 0.005 to 0.016. 
         FIG. 13  presents a computer result of said Model, wherein T 0 =400 K, the moles of H 2 O range from 0.021 to 0.063 and the moles of H 2  range from 0.005 to 0.016. 
         FIG. 14  presents a computer result of said Model, wherein T 0 =300 K, the moles of H 2 O range from 0.028 to 0.084 and the moles of H 2  range from 0.010 to 0.050. 
         FIG. 15  presents a computer result of said Model, wherein T 0 =300 K, the moles of H 2 O range from 0.028 to 0.084 and the moles of H 2  range from 0.060 to 0.100. 
         FIG. 16  presents a computer result of said Model, wherein T 0 =300 K, the moles of H 2 O range from 0.000 to 0.020 and the moles of H 2  range from 0.060 to 0.10. 
         FIG. 17  presents a computer result of said Model, wherein T 0 =300 K, the moles of H 2 O range from 0.100 to 0.0200 and the moles of H 2  range from 0.060 to 0.010. 
         FIG. 18  presents a flow diagram of the instant invention operating in the configuration of an internal combustion engine. Within  FIG. 18  are depicted two exhaust valves from each of said combustion chamber(s). It is an embodiment to operate the instant invention wherein each combustion chamber exhaust sends steam to a steam turbine, wherein said steam turbine turns at least one of a generator and an alternator, wherein the electricity created by said generator and/or said alternator is sent to an electrolysis unit, wherein the H 2 O in said electrolysis unit comprise condensate from the combustion of H 2  and O 2  in said combustion chamber, wherein said electrolysis unit converts said H 2 O into H 2  and O 2  for use in said combustion chamber. It is preferred to operate the instant invention wherein the combustion chamber exhaust sends steam to a condenser, wherein the water from said condenser is at least partially used in said combustion chamber. It is most preferred to operate the instant invention wherein the combustion chamber at least partially sends steam to a steam turbine, wherein said steam turbine turns at least one of a generator and an alternator, wherein the electricity created by said generator and/or said alternator is sent to an electrolysis unit, wherein the H 2 O in said electrolysis unit comprises condensate from the combustion of H 2  and O 2  in said combustion chamber, wherein said electrolysis unit converts said condensate into H 2  and O 2  for use in said combustion chamber, and wherein steam is at least partially sent to a condenser, wherein the H 2 O from said condenser is used in said combustion chamber. 
         FIG. 19  presents a flow diagram of the instant invention operating in the configuration of a steam turbine electrical power plant. It is to be understood that the H 2  fuel and the O 2  oxidizer for combustion in the steam turbine electrical power plant may be obtained from either storage of H 2  and/or O 2 , or creation of H 2  and/or O 2  from the electrolysis of water. In Space Applications, electrolysis of water is preferably performed with electrical energy obtained from photovoltaic cells or steam energy obtained from nuclear reaction. 
         FIG. 20  presents a flow diagram of the instant invention operating means as liquefaction for H 2  storage. It is to be understood that the same liquefaction means can be utilized for O 2  storage. 
     
    
    
     DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS 
     The timing of the instant invention is significant since humankind is preparing to travel to the Moon and to Mars. Timing of the instant invention is significant as a means is needed to improve H 2  and/or O 2  storage for extended space flight. Timing of the instant invention is significant as a means is needed to provide power to liquefaction means as a means to improve H 2  and/or O 2  storage for extended space flight. Timing of the instant invention is significant as travel to other planets by humanity requires improved power/engine mass ratios in order to improve the effectiveness of payloads to other worlds. 
     The instant invention utilizes the combustion of H 2  with O 2  to create energy. It is preferred that the methods, process, systems and apparatus of the instant invention produce at least one selected from a list consisting of: rotating mechanical energy, power, torque, and any combination therein. The instant invention utilizes H 2 O and/or the environmental temperature within a space application to cool the engine; H 2 O is preferably added to the combustion chamber, while utilizing the steam (hot gaseous H 2 O) produced during combustion and/or during cooling as a means of energy recycle and/or energy conservation by converting at least a portion of said steam energy into potential energy (fuel) for the instant invention. The combustion chamber is defined herein as a volume wherein combustion takes place or wherein the products of combustion create at least one of: energy, power, torque and any combination therein. Said recycled potential energy is to be at least one of O 2  and H 2 . 
     It is a preferred embodiment that combustion is at least one of internal combustion, open flame (heating) combustion and turbine combustion, as these applications are known in the art of combustion science.
     The Haase Cycle (Depicted in FIGS.  7  and  8 )—It is most preferred that the instant invention combust as a fuel H 2  with O 2  as the oxidant.   

     It is preferred that the instant invention be insulated to minimize enthalpy losses from the engine block. It is most preferred that the combustion chamber be insulated. It is most preferred that each combustion chamber be insulated, wherein there is at least one combustion chamber. It is preferred that the instant invention operate wherein H 2 O is added to the combustion chamber in order to cool and/or manage the temperature of the instant invention combustion chamber and/or engine block. It is most preferred that the instant invention operate wherein H 2 O is added to the combustion chamber during at least one of the expansion portion of the cycle and the exhaust portion of the cycle (or at a point in the expansion or exhaust portion of combustion in the case of a turbine) in order to cool and/or manage the temperature of said instant invention. It is most preferred that said H 2 O addition to combustion provide a reduction in combustion temperature to a temperature lower than that which would be obtained without the addition of H 2 O to combustion. It is most preferred that said H 2 O addition to combustion expands at least one of the P-V relationship, work, power, energy, torque, and any combination therein available from said instant invention. 
     It has been learned and is preferred in the instant invention that at least one selected from a list consisting of: reducing operating pressure, expanding P-V relationship, increasing available work, increasing available power, increasing available energy and any combination therein, can be performed by operating the instant invention with a Newsom burn. It is most preferred to operate the instant invention, wherein at least one of the H 2  and the O 2  is added during the generation of power (in the case of an internal combustion engine this would be defined as the power stroke). Further, due to the auto-ignition temperature of H 2 , which is approximately 585° C., it is most preferred to operate the instant invention without a spark or ignition device; such operation is defined herein defined as “diesel-like fashion.” 
     It is preferred to operate the instant invention with the addition of H 2 O to the combustion chamber during the exhaust stroke and/or to operate in diesel like fashion. It is most preferred to operate the instant invention in the configuration of an internal combustion engine, as is known in the art, wherein the instant invention operates with 2 cycles, as depicted in  FIG. 7 . It is preferred to operate instant invention in the configuration of an internal combustion engine, as is known in the art, wherein the number of cycles is 4, as depicted in  FIG. 8 . 
     It is most preferred that operation of the instant invention be in either diesel like fashion or in diesel like fashion with a slow bum situation by the addition of at least one of H 2  and O 2 , thereby creating a Newsom burn. It is preferred to operate the instant invention wherein at least one of H 2  and O 2  is added to the combustion chamber at a pressure of greater than about 0.1 atmosphere (1 atmosphere being 14.67 psia). It is preferred to operate the instant invention wherein at least one of H 2  and O 2  is added to the combustion chamber at a pressure of greater than about 1.0 atmosphere.
     Energy Recovery Cooling—It is an embodiment to perform cooling of the combustion chamber of the instant invention wherein H 2 O in the form of at least one of a liquid and a gas is added to the combustion chamber at a time before or after combustion. In the case of a turbine, as a turbine spins within a housing comprising 360° and the flame of the combustion chamber is located within at least one point of said 360° of said combustion housing, said H 2 O is preferably to be added to at least one point of said 360° of said combustion housing and in such an amount that said H 2 O cannot extinguish combustion flame. In the case of an internal combustion engine, it is preferred that said H 2 O be added to the combustion chamber during a cycle in which combustion does not occur, thereby cooling said combustion chamber with said H 2 O. (A cycle is herein defined as movement of the piston from top dead center (TDC) to full available piston displacement within the combustion cylinder and returning to TDC.) It is preferred to add said H 2 O to the combustion chamber in an internal combustion engine during a cycle in which combustion does not occur, the latent heat of vaporization of H 2 O is about 41 kJ/mole, as compared to the heat capacity of steam which is only about 34 J/(mole ° K). It is most preferred to add said H 2 O to the combustion chamber in an internal combustion engine during a cycle in which combustion does not occur for a number of cycles until a temperature within said combustion chamber is obtained; after which, a combustion cycle is repeated with H 2  and O 2 .   

     It is preferred that H 2 O added to the combustion cylinder of an internal combustion engine be added as near the beginning of the cycle (TDC) as is practical. As is revealed in the instant invention in examples 10 to 23, the available work from steam and the available cooling from adiabatic expansion of steam is directly related to the amount of adiabatic expansion of said steam in combination with the beginning temperature of said steam and the amount of said steam. It is preferred that there be at least one cycle in which H 2 O is added to the combustion chamber of an internal combustion engine. The number of cycles adding H 2 O to the combustion chamber of an internal combustion engine prior to the next combustion cycle is limited by the available enthalpy (measured as temperature) in the combustion chamber from the previous combustion cycle and the cooling effect of steam during adiabatic expansion of said steam. Depending on the beginning temperature, the amount of H 2 O converted to steam and the amount of adiabatic expansion, it is an embodiment that there a number of cycles of Energy Recovery Cooling, wherein said number can be from 1 to 20. It is preferred that H 2 O is added to the combustion chamber during at least one cycle or operating time wherein combustion is not performed and the H 2 O absorbs enthalpy from the combustion chamber, thereby creating steam energy and cooling the combustion chamber. 
     It is an embodiment that the materials of construction of the combustion chamber have a high heat transfer coefficient, such as that which is available with metals. Energy Recovery Cooling is most effective when the energy contained within the combustion chamber is easily transferred to the H 2 O, thereby creating steam energy. It is an embodiment that the materials of construction of the combustion chamber have a relatively high heat capacity, such as that which is available with metals. As the combustion chamber of the internal combustion engine is inherently inefficient loosing near 50 to 80 percent of the energy of combustion to heat and exhaust gases, Energy Recovery Cooling can most effectively improve engine power and efficiency when combustion heat energy, enthalpy, from the previous combustion cycle is stored within the material(s) of construction of the combustion chamber.
     Engine Efficiency—The instant invention utilizes electro-chemical pathways to convert H 2 O into O 2  and H 2 , wherein the electrical energy for these pathways is obtained from at least one of cooling the engine, exhaust gas energy, combustion output mechanical energy, photovoltaic energy and the energy of air or H 2 O motion. Given that the efficiency of most combustion engines (especially the internal combustion engine) is only approximately 15 to 25 percent (near 20 percent), the instant invention can significantly increase engine efficiency.   

     It is discovered that the theoretical limit of efficiency for the discovered WCT is approximately limited to the available enthalpy recovery during Energy Recovery Cooling minus friction losses. This theoretical limit presents that the theoretical efficiency limit of the instant invention to be near approximately 60-90 percent.
     Liquefaction—While liquefaction is commonly used in the chemical industry, liquefaction has not previously been used in Space Application(s), most notably in rocket fuel for rocket propulsion.   

     It is preferred to power a liquefaction unit with at least one of rotational mechanical energy and electricity. It is preferred that at least a portion of said rotational mechanical energy and/or electricity be generated by an engine of the instant invention. It is preferred that at least a portion of said rotational mechanical energy or electricity be generated by an engine of the instant invention, wherein combustion is cooled by the addition of H 2 O to the combustion chamber. It is preferred to perform liquefaction upon at least one of the H 2  and O 2  storage tanks in rocket prolusion with the liquefaction unit located on the rocket.
     Cryogenic Storage of H 2  and/or O 2 —It is a preferred embodiment to store at least one of O 2  and H 2  at a temperature of less than 0° C., herein referred to as cryogenic O 2  and cryogenic H 2 , respectively. It is preferred that said cryogenic O 2  and/or cryogenic H 2  be stored with a refrigeration and/or liquefaction loop. It is preferred that said refrigeration and/or liquefaction loop be powered by the stored cryogenic H 2  and O 2 . It is most preferred that said cryogenic O 2  and/or cryogenic H 2  be stored as a liquid or plasma.   Gel—It is preferred to improve the handling of H 2  by creating a H 2  gel. Said H 2  gel is to be formed by the inclusion of at least one selected from a list consisting of: H 2 O, O 2  and methane in said H 2 , wherein said H 2  is in a cryogenic state such that said inclusion is in a frozen crystalline state, thereby causing said H 2  and inclusion to form and behave as a gel. It is preferred to improve the handling of O 2  by creating an O 2  gel. Said O 2  gel is to be formed by the inclusion of at least one selected from a list consisting of: H 2 O, and methane in said O 2 , wherein said O 2  is in a cryogenic state such that said inclusion is in a frozen crystalline state, thereby causing said O 2  and inclusion to behave as a gel.   Insulation—It is preferred to insulate an engine of the instant invention. It is preferred to insulate an engine of the instant invention, wherein said engine is cooled by the addition of H 2 O to the combustion chamber.   

     It is most preferred that said insulation be that as is known in the art. It is preferred that said insulation be located around each combustion chamber to thereby minimize the use of high temperature materials in construction of the instant invention. In the case of an ICE, it is preferred that each combustion chamber (most likely of cylinder type design) be insulated with insulation materials as known in the art of insulation. In the case of an ICE, it is preferred that each combustion chamber (most likely of cylinder type design) be insulated with insulation materials as known in the art of insulation, wherein said insulation materials slow the rate of heat transfer from said combustion chamber via a shape of insulation material which is cylindrical and which surrounds said combustion chamber. In the case of an ICE, it is preferred that each combustion chamber (most likely of cylinder type design) be insulated with insulation materials as known in the art of insulation, wherein the piston contains a layer of insulation to reduce the rate of heat transfer from the combustion chamber into the block of the engine. In the case of an ICE, it is preferred that each combustion chamber (most likely of cylinder type design) be insulated with insulation materials as known in the art of insulation, wherein the head components of said ICE comprise a layer of insulation to reduce the rate of heat transfer from the combustion chamber to said head components or to the surrounding environment. In the case of an ICE, it is preferred that each combustion chamber (most likely of cylinder type design) be insulated with insulation materials as known in the art of insulation, wherein said ICE is cool externally to the touch. In the case of an ICE, it is preferred that each combustion chamber (most likely of cylinder type design) be insulated with insulation materials as are known in the art of insulation, wherein said ICE is externally cool to the touch, wherein the external surface temperature of said ICE is at least about less than 150° F. In the case of a turbine, it is preferred that each combustion chamber (most likely of cylinder type design) be insulated with insulation materials as are known in the art of insulation. 
     It is preferred that ceramic materials are used. A ceramic material is herein defined as a compound comprising at least one metal, other than iron, which forms a crystalline structure, wherein said crystalline structure is formed by heat.
     Steam Conversion—It is preferred to convert exhaust gas H 2 O, steam, into H 2  utilizing corrosion to chemically convert the steam to H 2 . Said corrosion is to utilize the O 2  in the steam to convert at least one metal to its metal oxide, while releasing H 2 . It is most preferred to produce an electromotive potential in at least one metal to drive the corrosion process for the at least one metal to its metal oxide, while producing H 2 . It is most preferred that said electromotive potential be anodic.   Electrolysis—It is preferred to electro-chemically convert exhaust gas H 2 O into O 2  and H 2 . It is to be understood that under the best of engineered circumstances, the electrical energy required by electrolysis to convert H 2 O into O 2  and H 2  will be greater than the energy obtained by the combustion of O 2  and H 2 . However, electrolysis allows for significant improvements in the thermodynamic efficiency of combustion by reclaiming energy which would otherwise be lost.   

     As the installation of a steam turbine in the engine exhaust will create a back pressure situation to the engine, thereby lessening engine power and efficiency, it is preferred that the instant invention include a condenser, thereby evacuating the combustion chamber and minimizing combustion chamber pressure prior to the next combustion cycle. It is most preferred that the condenser for steam exiting the steam turbine and the condenser for the steam evacuating the combustion chamber be the same condenser. It is an embodiment that the condenser for steam exiting the steam turbine be separate from the condenser for the steam evacuating the combustion chamber. It is preferred that make-up H 2 O to the instant invention be added to at least one of said condenser(s). It is preferred that the H 2 O added to the combustion chamber comprise H 2 O from said condenser(s). It is preferred that at least a portion of the H 2  in said condenser(s) be transferred to an electrolysis unit. It is preferred that the H 2 O in said electrolysis unit be converted to H 2  and O 2  by electrolysis. It is preferred that at least a portion of said H 2  be used as a fuel in said combustion chamber. It is preferred that at least a portion of said O 2  be used as an oxidizer in said combustion chamber. It is most preferred that the electrical energy of said electrolysis unit be obtained from at least one of an alternator and a generator wherein the power to turn said at least one of an alternator and a generator be obtained from at least one selected from a list consisting of a steam turbine turned by the exhaust gases (steam) from the combustion chamber(s), a drive shaft turned by the combustion chambers, moving wind energy, moving H 2 O energy, and any combination therein.
     Electrolysis Electrical Energy—It is preferred to obtain the electrical energy for electrolysis from at least one method selected from a list consisting of: rotating mechanical energy turning a generator, exhaust gas steam energy turning turbine which turns a generator, light energy via a photovoltaic cell, wind energy (moving air) turning a turbine which turns an electrical generator, and nuclear energy creating steam which turns a turbine which turns a generator, and any combination therein. It is most preferred that said rotating mechanical energy comprise rotating mechanical energy created by an engine using H 2  as a fuel and O 2  as an oxidizer. It is most preferred that said rotating mechanical energy comprise rotating mechanical energy created by an engine using H 2  as a fuel and O 2  as an oxidizer, wherein said engine is cooled by the addition of H 2 O to the combustion chamber.   Potential Energy/Fuel Generation—It is most preferred that at least a portion of the H 2  and/or O 2  from the electrolysis of H 2 O be used in an engine using H 2  as a fuel and O 2  as an oxidizer. It is most preferred that at least a portion of the H 2  and/or O 2  from the electrolysis of H 2 O be used in an engine using H 2  as a fuel and O 2  as an oxidizer, wherein said engine is cooled by the addition of H 2 O to the combustion chamber.   Electricity Generation—It is preferred to generate electrical energy, wherein said electrical energy (electricity) is created from a generator, wherein said generator is turned by rotating mechanical energy, wherein said rotating mechanical energy is created by an engine using H 2  as a fuel and O 2  as an oxidizer. It is preferred to generate electricity, wherein said electricity is created from a generator, wherein said generator is turned by rotating mechanical energy, wherein said rotating mechanical energy is created by an engine using H 2  as a fuel and O 2  as an oxidizer, wherein said engine is cooled by the addition of H 2 O to the combustion chamber.   

     It is a preferred embodiment that said rotating mechanical rotating energy enter a transmission, wherein said transmission engage in a manner that is inversely proportional to the torque and/or work load of the engine, wherein said transmission output mechanical rotating energy turn said generator to create said electrical energy. Said transmission is to be as is known in the art. It is most preferred that said transmission engage a flywheel capable of storing rotational kinetic energy, wherein said flywheel turns said generator. 
     It is preferred to generate electricity, wherein said electricity is created from a generator, wherein said generator is turned by a steam turbine, wherein said steam turbine is turned by steam, wherein said steam is created by an engine using H 2  as a fuel and O 2  as an oxidizer. It is preferred to generate electricity, wherein said electricity is created from a generator, wherein said generator is turned by a steam turbine, wherein said steam turbine is turned by steam, wherein said steam is created by an engine using H 2  as a fuel and O 2  as an oxidizer, wherein said engine is cooled by the addition of H 2 O to the combustion chamber. It is preferred that said steam turbine(s) be in such a configuration that said steam be the exhaust of said engine. It is preferred that said steam energy be converted into rotational mechanical energy via a turbine to turn said generator. It is most preferred that there be at least one steam turbine and that said steam turbine(s) create mechanical energy to turn at least one of said generator(s). 
     It is preferred to generate electricity by the energy of light using photovoltaic cells, wherein said electricity is used to electrochemically convert H 2 O into H 2  and O 2 , and wherein at least one of said H 2  and O 2  is used in the combustion chamber of the instant invention. 
     It is preferred to generate electricity by nuclear means, wherein said nuclear means is defined herein as the generation of heat energy generated from the radioactive decay of at least one element or the generation of He from H 2 , wherein said heat energy is used to create steam energy, wherein said steam energy is used to turn at least one steam turbine, and wherein said steam turbine turns at least one generator to create said electricity. It is preferred that said electricity is used to electrochemically convert H 2 O into H 2  and O 2 , wherein at least one of said H 2  and O 2  is used in the combustion chamber of the instant invention. 
     It is preferred to generate electricity, wherein said electricity is generated by at least one selected from a list consisting of photovoltaic cells, moving air, moving H 2 O, nuclear means and any combination therein, wherein said electricity is at least partially utilized in an electrolysis unit to convert H 2 O to H 2  and O 2 , and wherein at least a portion of at least one of said H 2  and O 2  is used in the combustion chamber of the instant invention.
     H 2 O Chemistry—H 2 O is the most efficient and economical method of storing O 2  and/or H 2 . Electrolysis is the most preferred method of converting H 2 O into combustible H 2  and O 2 .   

     Electrolysis is best performed with a dissolved electrolyte in the H 2 O; the dissolved electrolyte, most preferably a salt, will improve conductivity in the H 2 O, thereby reducing the required electrical energy to perform electrolysis. It is an embodiment to perform electrolysis upon H 2 O that contains an electrolyte. It is preferred to perform electrolysis upon H 2 O that contains a salt. It is most preferred to perform electrolysis upon H 2 O that contains polyelectrolytes. 
     However, many dissolved cation(s) and anion(s) combination(s) can precipitate over time reducing the efficiency of electrolysis. Further, as temperature is increased, hard H 2 O contaminants may precipitate; therefore, it is preferred to add a dispersant to the H 2 O to prevent scale. 
     Dispersants are low molecular weight polymers, usually organic acids having a molecular weight of less than 25,000 and preferably less than 10,000. Dispersants are normally polyelectrolytes. Dispersant chemistry is based upon carboxylic chemistry, as well as alkyl sulfate, alkyl sulfite and alkyl sulfide chemistry; it is the oxygen (O) atom that creates the dispersion, wherein O takes its form in the molecule as a carboxylic moiety and/or a sulfoxy moiety. Dispersants that can be used in the instant invention which contain the carboxyl moiety comprise at least one selected from a list consisting of acrylic polymers, acrylic acid, polymers of acrylic acid, methacrylic acid, maleic acid, furnaric acid, itaconic acid, crotonic acid, cinnamic acid, vinyl benzoic acid, any polymers of these acids and any combination therein. Dispersants that can be used in the instant invention contain the alkyl sulfoxy or allyl sulfoxy moieties include any alkyl or allyl compound, comprise at least one selected from a list consisting of SO, SO 2 , SO 3  and any combination therein. Due to the many ways in which an organic molecule can be designed to contain the carboxyl moiety and/or the sulfoxy moiety, it is an embodiment that any H 2 O soluble organic compound containing at least one of a carboxylic moiety and/or a sulfoxy moiety may be added to the H 2 O in the instant invention. (This is with the knowledge that not all dispersants have equivalent dispersing properties. Acrylic polymers exhibit very good dispersion properties, thereby limiting the deposition of H 2 O soluble salts and are most preferred embodiments as a dispersant. The limitation in the use of a dispersant is in the H 2 O solubility of the dispersant in combination with its carboxylic nature and/or sulfoxy nature.) 
     H 2 O is inherently corrosive to metals. H 2 O naturally oxidizes metals, some with a greater oxidation rate than others. To minimize corrosion, it is preferred that the H 2 O have a pH of equal to or greater than 7.5, wherein the alkalinity of the pH is obtained from the hydroxyl anion. Further, to prevent corrosion or deposition of H 2 O deposits on steam turbines, it is preferred to add a corrosion inhibitor to the H 2 O. It is an embodiment to utilize nitrogen (N) containing corrosion inhibitors, such as hydrazine, as is known in the art of H 2 O treatment. 
     While corrosion inhibitors are added to H 2 O to prevent corrosion, a chelant is preferred to both prevent corrosion and complex, as well as prevent the deposition of, a cation, including hardness and heavy metals. A chelant or a chelating agent is a compound having or forming a heterocyclic ring wherein at least two kinds of atoms are joined in a ring. Chelating is forming a heterocyclic ring compound by joining a chelating agent to a metal ion. Most chelants are polyelectrolytes. It is a preferred embodiment to use a chelant in the H 2 O and or the steam to control mineral deposition. It is preferred to add to the H 2 O and/or the steam at least one selected from a list consisting of a: phosphate, phosphate polymer, phosphate monomer and any combination thereof. Said phosphate polymers consist of, but are not limited to, phosphoric acid esters, metaphosphates, hexametaphosphates, pyrophosphates and/or any combination thereof. Phosphate polymers are particularly effective in dispersing magnesium silicate, magnesium hydroxide and calcium phosphates. Phosphate polymers are particularly effective at corrosion control. With proper selection of a polymer, along with maintaining an adequate polymer concentration level, the surface charge on particle(s) can be favorably altered. In addition to changing the surface charge, polymers also function by distorting crystal growth.
     Operating Pressure Management—An engine recycling exhaust gas energy has the potential to develop unintended operating situations, wherein the operating pressure becomes greater than the design pressure of the equipment employed; any such situation can be a significant safety issue. And, regardless of a safety situation, the recycling of exhaust gas energy from an engine which may operate in a situation of changing exhaust gas conditions, comprises a situation wherein the pressure of said exhaust gas should be managed in order to protect equipment and manage equipment operation. Operating pressure management is to include a pressure management device, herein termed a pressure control device, which may include any type of pressure controller and/or pressure relief device as is known in the art of managing gas pressure. Such devices can include, yet are not limited to: a pressure control valve, a pressure control loop including a valve, a relief valve, a rupture disc and any combination therein. It is an embodiment to provide a pressure control device to an engine using H 2  as a fuel and O 2  as an oxidizer. It is an embodiment to provide a pressure control device to an engine using H 2  as a fuel and O 2  as an oxidizer, wherein said engine is cooled by the addition of H 2 O to the combustion chamber. It is an embodiment to provide a pressure control device to an engine using H 2  as a fuel with air as the oxidizer, wherein said air is in excess over that required to perform combustion to limit NO X  formation. It is a preferred embodiment to provide a pressure control device to an engine using H 2  as a fuel and O 2  as an oxidizer, wherein the exhaust gas of said engine comprises steam, and wherein said steam turns a steam turbine. It is a preferred embodiment to provide a pressure control device to an engine using H 2  as a fuel and O 2  as an oxidizer, wherein said engine is cooled by the addition of H 2 O to the combustion chamber, wherein the exhaust gas of said engine comprises steam, and wherein said steam turns a steam turbine.   Engine, H 2 O and Lubricant Heating—In Space Applications, as the ambient temperature is often below the freezing point of water and of an engine lubricant, it is preferred to provide a means of heating to at least one of: any engine block, engine water and engine lubricant. It is most preferred that said means of heating be accomplished by a heating element powered by a fuel cell and/or of combustion heat energy obtained from the instant invention. It is most preferred that said fuel cell be powered by H 2  and O 2 . It is most preferred that said fuel cell provide said means of heating via a resistive wire type of heating element, as is known in the art It is most preferred that at least one of said engine block, said engine H 2 O and said engine lubricant be insulated from ambient temperature. It is most preferred that said fuel cell be a fuel cell as is known in the art.   Apparatus—Referring to  FIG. 6 , a combustion engine is symbolically shown for receiving as fuel H 2  and as an oxidizer O 2 . Said combustion engine may be of any type, wherein combustion is performed to generate at least one of mechanical torque, heat, thrust, electricity and/or any combination therein. It is preferred that said H 2  to the combustion chamber is to have a flow. O 2  flowing to the combustion chamber is to have a flow. There is to be means to measure said H 2  flow and a means to measure said O 2  flow, such that a proportional signal in relation to said flows is sent to a controller from each of said H 2  flow measuring device and said O 2  flow measuring device. H 2  flowing to the combustion chamber is to have at least one flow control valve. O 2  flowing to the combustion chamber is to have at least one flow control valve. Each flow measuring device is to create a flow signal. A controller is to have as input said H 2  flow signal and said O 2  flow signal. Said controller is to receive an input signal from an external source indicating the combustion setpoint. Said controller is to compare said combustion setpoint to said H 2  flow signal and/or to said engine rpm, sending a proportional signal to said H 2  flow control valve that is in proportion to the difference in said combustion setpoint and the said flow signal, thereby proportioning said H 2  flow control valve. The controller is to compare said O 2  flow signal to an H 2  ratio setpoint, providing a proportional signal to said O 2  flow control valve, wherein said H 2  flow and said O 2  flow are such that the molar ratio of H 2  to O 2  is approximately 2:1.   

     To conserve energy, it is most preferred that said H 2  flow control valve(s) consist of a two staged system of flow control valves. The first H 2  flow control valve is to control recycled H 2  to the combustion chamber, The first H 2  control valve is preferably to be downstream of generated H 2  and downstream of H 2  storage to control H 2  flow to the combustion chamber. The second H 2  flow control valve is to feed stored H 2  to the combustion chamber. The second H 2  flow control valve is preferably to remain closed until the first H 2  flow control valve is near approximately 100% open (thereby assuring about full usage of generated H 2  prior usage of stored H 2 ) at which time the second H 2  flow control valve will begin proportion by the controller according to the H 2  setpoint flow control signal. It is also preferred that a recycle H 2  control valve be placed to control the recycle of H 2  to H 2  storage. Said recycle H 2  control valve is to be proportional to the first H 2  control valve position near 100% closed. It is preferred that said controller proportion said recycle H 2  control valve in relation to the first H 2  control valve near a 0 position or 100% closed. 
     To conserve energy, it is preferred that said O 2  flow control valve(s) consist of a two staged system of flow control valves. The first O 2  flow control valve, downstream of generated O 2  and downstream of H 2  storage is preferably to control H 2  flow to the combustion chamber. The second H 2  flow control valve is to feed stored O 2  to the combustion chamber. The second H 2  flow control valve is to remain closed until the first O 2  flow control valve is near approximately 100% open (thereby assuring full usage of generated O 2  prior usage of stored O 2 ) at which time the second O 2  flow control valve will begin proportioned by the controller according to the H 2  setpoint flow control signal. It is also preferred that a recycle O 2  control valve be placed to control the recycle of O 2  to O 2  storage. Said recycle O 2  control valve is to be proportional to the first O 2  control valve position near 100% closed. It is preferred that said controller proportion said recycle O 2  control valve in relation to the first O 2  control valve near a 0 position or 100% closed. 
     It is preferred that said combustion comprise an available H 2 O flow to said combustion chamber(s), herein termed as combustion H 2 O. It is preferred that a temperature measurement device have a means of measuring combustion temperature or approximating combustion temperature. It is preferred that there is a means to measure said combustion H 2 O flow. It is preferred that there is a means to indicate engine rpm. It is preferred to send a signal to a controller from each of said combustion H 2 O flow measuring device and said combustion temperature measuring device. Said controller is to have as input previous said H 2  flow signal, said engine rpm, said combustion H 2 O flow signal and said combustion temperature signal. It is preferred that said controller have a hot temperature setpoint, a warm temperature setpoint, an engine rpm setpoint and an H 2 /H 2 O ratio setpoint. It is most preferred that said controller compare said H 2  flow signal and said combustion H 2 O flow signal to said H 2 /H 2 O ratio setpoint in combination with comparing said engine rpm signal to said engine rpm setpoint, temperature signal to said warm temperature setpoint, said hot temperature setpoint and provide a proportional signal to said combustion H 2 O flow control vale and to said coolant flow control valve. 
     In the case wherein said temperature signal is less than said warm temperature setpoint, and less than said hot temperature setpoint, it is preferred that said controller send a signal to said combustion H 2 O flow control valve to close said combustion H 2 O flow control valve. 
     In the case wherein said H 2 /H 2 O ratio is about greater than said H 2 /H 2 O ratio setpoint and said temperature signal is about equal to or greater than said warm temperature setpoint, less than said hot temperature setpoint and engine rpm signal is greater than said engine rpm setpoint, it is preferred that said controller send a signal to said combustion H 2 O flow control valve, wherein said signal is proportional to the difference between said measured temperature signal and the warm temperature setpoint, thereby proportioning said combustion H 2 O flow control valve. 
     In the case wherein said H 2 /H 2 O ratio is about greater than said H 2 /H 2 O ratio setpoint and said temperature signal is greater than said warm temperature setpoint and equal to or greater than said hot temperature setpoint, it is preferred that said controller send a signal to: close the combustion H 2 O flow control valve; and send a signal to said H 2  flow control valve, thereby closing said H 2  flow control valve; and send a signal to said O 2  flow control valve, thereby closing said O 2  flow control valve:. 
     It is most preferred that the engine operate at a temperature between said warm temperature setpoint and said coolant temperature setpoint. It is preferred that energy not leave the engine via engine coolant. It is most preferred that required engine cooling be performed by the addition of combustion H 2 O to the combustion chamber(s). 
     Materials of construction for the engine are to be those as known in the art for each application as said application is otherwise performed in the subject art. For example, various composite and metal alloys are known and used as materials for use at cryogenic temperatures. Various composite, ceramic and metal alloys are known and used as materials for use at operating temperatures of over 500° F. Various ceramic materials can be conductive, perform at operating temperatures of over 2,000° F., act as an insulator, act as a semiconductor and/or perform other functions. Various iron compositions and alloys are known for their performance in combustion engines that operate approximately in the 200 to 1,000° F. range. Titanium and titanium alloys are known to operate over 2,000 and 3,000° F. Tantalum and tungsten are known to operate well over 3,000° F. It is preferred to have at least a portion of the construction of the engine contain an alloy composition wherein at least one of a period 4, period 5 and/or a period 6 heavy metal is used, as that metal(s) is known in the art to perform individually or to combine in an alloy to limit corrosion and/or perform in a cryogenic temperature application and/or perform in a temperature application over 1,000° F. While aluminum is lightweight and can perform in limited structural applications, aluminum is temperature limited. Due to the operating temperatures involved in the instant invention, thermoplastic materials are not preferred unless the application of use takes into account the glass transition temperature and the softening temperature of the thermoplastic material. 
     Example 1 presents the Otto Cycle modified for the instant invention engine in an internal combustion application. Examples 2 through 9 present results obtained via a computer model of the WCT engine developed according the presentation and results within Example 1. Said computer model was prepared with an Excel spreadsheet program, incorporating graphing capabilities. Said computer model was prepared incorporating the thermodynamic properties of H 2 , O 2  and H 2 O, along with the thermodynamic relationships presented in Example 1. 
     Example 1 
     An Excel Spreadsheet Computer Model has been prepared for the instant invention. Said Model is the product of this Example in the instant invention, the results of which are presented in Examples 2 through 9. 
     Operation of the instant invention is approximated by the cycling of a 4 stroke internal combustion engine as depicted in  FIG. 9 , wherein path a to b presents an intake stroke during which a H 7 O vapor-fuel-oxidizer mixture is drawn into the combustion chamber as the piston moves outward. Next, the intake valve closes, wherein the piston moves inward thereby compressing the H 2 O vapor, fuel and oxidizer mixture; this is depicted to be along the path from point “0” to point “1”. This is process is about adiabatic since it occurs rapidly. 
     At approximately near the end of the compression stroke, the mixture is ignited and the pressure increases rapidly along the path from point 1 to point 2. This process happens very quickly, thereby being nearly a pure isochoric (constant volume) process. 
     The power stroke is next, wherein the power stroke is about an adiabatic expansion from point 2 to point 3. At the end of the power stroke, the exhaust valve is opened, wherein the exhaust gases escape in an approximately isochoric process moving along the path from point 3 to point 4. 
     Finally, the piston again moves inward, thereby forcing exhaust gases out of the combustion chamber along the path b to a. And the cycle repeats . . . . 
     As net work is the product of pressure and volume, the net work performed is approximated by the area enclosed by the four path points: 0 to 1, 1 to 2, 2 to 3, and 3 to 4. The work done during the intake and exhaust strokes (the areas under paths a to b and b to a) cancel each other. 
     In this example, the instant invention comprises: 
     
       
         
           
               
               
               
             
               
                   
                   
               
             
            
               
                   
                 Number of cylinders 
                  6 
               
               
                   
                 Bore 
                 100.0 mm 
               
               
                   
                 Stroke 
                  78.9 mm 
               
               
                   
                 Compression ratio 
                 10 
               
               
                   
                   
               
            
           
         
       
     
     Compression 
     
       
         
           
             
               Engine 
                
               
                   
               
                
               displacement 
             
             = 
             
               π 
               · 
               
                 
                   ( 
                   
                     bore 
                     2 
                   
                   ) 
                 
                 2 
               
               · 
               
                 ( 
                 stroke 
                 ) 
               
               · 
               
                 ( 
                 
                   # 
                    
                   
                       
                   
                    
                   of 
                    
                   
                       
                   
                    
                   
                     cyls 
                     . 
                   
                 
                 ) 
               
             
           
         
       
       
         
           
             
               
                 
                   
                     Displacement 
                      
                     
                         
                     
                      
                     per 
                      
                     
                         
                     
                      
                     cylinder 
                   
                   = 
                   
                     π 
                     · 
                     
                       
                         ( 
                         
                           50 
                            
                           
                               
                           
                            
                           mm 
                         
                         ) 
                       
                       2 
                     
                     · 
                     
                       ( 
                       
                         78.9 
                          
                         
                             
                         
                          
                         mm 
                       
                       ) 
                     
                   
                 
               
             
             
               
                 
                   = 
                   
                     620 
                      
                     
                         
                     
                      
                     
                       cm 
                       3 
                     
                      
                     
                         
                     
                      
                     
                       ( 
                       
                         0.62 
                          
                         
                             
                         
                          
                         l 
                       
                       ) 
                     
                   
                 
               
             
           
         
       
       
         
           
             
               Compression 
                
               
                 
                     
                 
                  
                 
                     
                 
               
                
               ratio 
             
             = 
             
               
                 c 
                 . 
                 r 
                 . 
               
               = 
               
                 
                   displacement 
                   + 
                   
                     dead 
                      
                     
                         
                     
                      
                     space 
                   
                 
                 
                   dead 
                    
                   
                       
                   
                    
                   space 
                 
               
             
           
         
       
     
     The dead space (volume remaining when the piston is fully inserted can be calculated from: 
     
       
         
           
             
               c 
               . 
               r 
               . 
             
             = 
             
               10.0 
               = 
               
                 
                   
                     620 
                     + 
                     
                       d 
                       . 
                       s 
                       . 
                     
                   
                   
                     d 
                     . 
                     s 
                     . 
                   
                 
                 → 
                 
                   69 
                    
                   
                       
                   
                    
                   
                     mm 
                     3 
                   
                    
                   
                       
                   
                    
                   
                     ( 
                     
                       0.069 
                        
                       
                           
                       
                        
                       l 
                     
                     ) 
                   
                 
               
             
           
         
       
     
     For simplicity we&#39;ll approximate 0.070 L for the dead space. 
     In this example, it is assumed that the intake mixture consists of H 2 O vapor, oxidizer (O 2 ) and fuel (H 2 ). It is an embodiment that the intake mixture comprises H 2 O vapor, wherein the oxidizer could be injected at any point during at least one of the compression stroke and the power stroke. Similarly, it is also an embodiment that the fuel could be injected at any point during at least one of the compression stroke and the power stroke. In this example it is assumed and is a preferred embodiment that the pressure at the beginning of the compression stroke is about 1 atmosphere. It is a most preferred embodiment that the pressure at the beginning of the compression stroke is greater than about 1 atmosphere. It is an embodiment that the pressure at the beginning of the compression stroke is about less than 1 atmosphere. 
     Again, in this example the embodiment comprising an intake mixture consists of H 2 O vapor, O 2  and H 2  at 1 atmosphere pressure is depicted. In this depiction we can approximate the number of moles of H 2 O vapor, fuel and O 2  in the cylinder at the beginning of the compression stroke from the ideal gas law. 
     
       
         
           
             n 
             = 
             
               
                 P 
                 · 
                 V 
               
               
                 R 
                 · 
                 T 
               
             
           
         
       
       
         
           
             n 
             = 
             
               
                 
                   
                     ( 
                     
                       1.0 
                        
                       
                           
                       
                        
                       atm 
                     
                     ) 
                   
                   · 
                   
                     ( 
                     
                       0.69 
                        
                       
                           
                       
                        
                       l 
                     
                     ) 
                   
                 
                 
                   
                     ( 
                     
                       
                         0.0821 
                          
                         
                             
                         
                          
                         l 
                       
                       - 
                       
                         atm 
                         / 
                         mole 
                       
                       - 
                       K 
                     
                     ) 
                   
                   · 
                   
                     ( 
                     
                       300 
                        
                       
                           
                       
                        
                       K 
                     
                     ) 
                   
                 
               
               = 
               
                 0.0280 
                  
                 
                     
                 
                  
                 moles 
               
             
           
         
       
     
     And, the pressure in the cylinder at the end of the compression stroke can be approximate by: 
     
       
         
           
             
               P 
               · 
               
                 V 
                 γ 
               
             
             = 
             
               constant 
               = 
               
                 
                   P 
                   0 
                 
                 · 
                 
                   V 
                   0 
                   γ 
                 
               
             
           
         
       
       
         
           
             P 
             = 
             
               
                 P 
                 0 
               
               · 
               
                 
                   ( 
                   
                     
                       V 
                       0 
                     
                     V 
                   
                   ) 
                 
                 γ 
               
             
           
         
       
       
         
           
             P 
             = 
             
               
                 
                   ( 
                   
                     1.0 
                      
                     
                         
                     
                      
                     atm 
                   
                   ) 
                 
                 · 
                 
                   
                     ( 
                     
                       
                         0.690 
                          
                         
                             
                         
                          
                         l 
                       
                       
                         0.070 
                          
                         
                             
                         
                          
                         l 
                       
                     
                     ) 
                   
                   1.4 
                 
               
               = 
               
                 24.6 
                  
                 
                     
                 
                  
                 atm 
               
             
           
         
       
     
     The temperature in the combustion chamber at the end of compression can be approximated by: 
     
       
         
           
             T 
             = 
             
               
                 P 
                 · 
                 V 
               
               
                 n 
                 · 
                 R 
               
             
           
         
       
       
         
           
             T 
             = 
             
               
                 
                   ( 
                   
                     24.6 
                      
                     
                         
                     
                      
                     atm 
                   
                   ) 
                 
                 · 
                 
                   ( 
                   
                     0.070 
                      
                     
                         
                     
                      
                     l 
                   
                   ) 
                 
               
               
                 
                   ( 
                   
                     0.0280 
                      
                     
                         
                     
                      
                     moles 
                   
                   ) 
                 
                 · 
                 
                   ( 
                   
                     
                       0.0821 
                        
                       
                           
                       
                        
                       l 
                     
                     - 
                     
                       
                         atm 
                         / 
                         mole 
                       
                       · 
                       K 
                     
                   
                   ) 
                 
               
             
           
         
       
       
         
           
             T 
             = 
             
               749.1 
                
               
                   
               
                
               K 
             
           
         
       
     
     with the resulting curve in  FIG. 9 .
 
Combustion—The chemical reaction between H 2  and O 2  can be approximated by:
 
       2H 2 +O 2 →2H 2 O+137 kcal
 
     In this example, it is assumed that near 0.0280 moles of H 2 , O 2  and H 2 O are in the cylinder (for this example, knowing that there may be more or less); it is further assumed that the gas mixture comprises about 18% O 2 , 36% H 2  and 46% H 2 O vapor (for this example, knowing that there may be more or less of each, except it is most preferred that the H 2  be about near twice the concentration of the O 2 ). It is an embodiment that these percentages may be varied as needed; however, it is most preferred that the molar concentration of H 2  be about near twice the molar concentration of the O 2 . Therefore, in this example the combustion chamber comprises about 0.0050 moles of O 2  along with 0.0100 moles of H 2 ; and, assuming near complete combustion, said near 0.0050 moles of O 2  and said near 0.0100 moles of H 2  should yield about 2.87 kJ of energy. And, since about no work is done during combustion, the first law of thermodynamics requires that said 2.87 kJ be retained as internal energy of the reaction products which will raise their temperatures in proportion to the number of moles present and the specific heat of the gas. For H 2 O is about: 0.0280 moles with a heat capacity of about 36.2 J/mole-K. The temperature rise is then approximated by: 
       Δ T=Q /( n   H     2     O   ·C   H     2     O )
 
       Δ T= 2.87 kJ/(0.0280.36.2)=2831 K
 
     Since the temperature at the start of the combustion was estimated near 749.1 K, the final temperature following combustion is about 749.1 K+2831 K or 3580 K. Having an approximation of the temperature rise, the final pressure is approximated from the ideal gas law and the total number of moles of gases present: 
     
       
         
           
             
               
                 
                   Pressure 
                   = 
                   
                     
                       
                         ( 
                         
                           0.0280 
                            
                           
                               
                           
                            
                           moles 
                         
                         ) 
                       
                       · 
                       
                         ( 
                         
                           
                             0.0821 
                              
                             
                                 
                             
                              
                             l 
                           
                           - 
                           
                             atm 
                             / 
                             mole 
                           
                           - 
                           K 
                         
                         ) 
                       
                       · 
                       
                         ( 
                         
                           3580 
                            
                           
                               
                           
                            
                           K 
                         
                         ) 
                       
                     
                     
                       0.070 
                        
                       
                           
                       
                        
                       l 
                     
                   
                 
               
             
             
               
                 
                   = 
                   
                     117.6 
                      
                     
                         
                     
                      
                     atm 
                      
                     
                         
                     
                      
                     
                       ( 
                       
                         1728 
                          
                         
                             
                         
                          
                         psi 
                       
                       ) 
                     
                   
                 
               
             
           
         
       
     
     The increase in pressure from 24.6 atm to 117.6 atm is near constant volume and is depicted as the vertical line from point 1 to point 2 on the P-V diagram of  FIG. 9 . Expansion - Having approximated the pressure at the beginning of the expansion stroke (and knowing the volume) it is possible to approximate the pressure as a function of volume during the expansion: 
     
       
         
           
             P 
             = 
             
               
                 P 
                 0 
               
               · 
               
                 
                   ( 
                   
                     
                       V 
                       0 
                     
                     V 
                   
                   ) 
                 
                 γ 
               
             
           
         
       
       
         
           
             P 
             = 
             
               
                 ( 
                 
                   117.6 
                    
                   
                       
                   
                    
                   atm 
                 
                 ) 
               
               · 
               
                 
                   ( 
                   
                     
                       0.070 
                        
                       
                           
                       
                        
                       l 
                     
                     V 
                   
                   ) 
                 
                 1.4 
               
             
           
         
       
     
     This line is depicted as the line from point 2 to point 3 on the P-V diagram,  FIG. 9 . Exhaust—The exhaust stroke is depicted from point 3 to point 0 on the P-V diagram of  FIG. 9 . Work Performed—Work is only done by (or on) the system during the adiabatic processes which can be approximated as follows: 
     
       
         
           
             W 
             = 
             
               ∫ 
               
                 P 
                 · 
                 
                    
                   V 
                 
               
             
           
         
       
       
         
           
             
               P 
               · 
               
                 V 
                 γ 
               
             
             = 
             
               
                 P 
                 0 
               
               · 
               
                 V 
                 0 
               
             
           
         
       
       
         
           
             
               W 
               = 
               
                 ∫ 
                 
                   
                     
                       
                         P 
                         0 
                       
                        
                       
                         ( 
                         
                           
                             V 
                             0 
                           
                           V 
                         
                         ) 
                       
                     
                     γ 
                   
                   · 
                   
                      
                     V 
                   
                 
               
             
             , 
             
                 
             
              
             where 
           
         
       
       
         
           
             W 
             = 
             
               
                 
                   
                     
                       P 
                       0 
                     
                     · 
                     V 
                   
                   
                     1 
                     - 
                     γ 
                   
                 
                  
                 
                   
                     ( 
                     
                       
                         V 
                         0 
                       
                       V 
                     
                     ) 
                   
                   γ 
                 
               
                
               
                  
                 
                   V 
                   i 
                 
                 
                   V 
                   f 
                 
               
             
           
         
       
     
                                                     Parameter   Compression   Expansion   Units                                                            P 0     1.0   117.6   atm           V 0  (V i )   0.690   0.070   liters           Vf   0.070   0.690   liters           Work   −2.42   12.35   l-atm                        
Therefore, the net work performed during each cycle is 12.35-2.42 L-atm, 9.93 L-atm (1.006 kJ). Total horsepower—For a typical automobile running at 60 MPH the engine speed is approximately 3000 rpm is near 50 revolutions per second (this approximation can be modified for alternate rpm situations given alternate transmission situations). Since in a 4 stroke engine a cylinder has a power stroke only every other revolution, it will be firing at a rate of 25 power strokes per second. A six-cylinder engine will then have 150 power strokes per second. Thus, the total power will be near
 
       (150 power strokes/sec)·(1.006 kJ/stroke)/0.746 kW/hp=202 hp
 
     And, in a 2 stroke engine near twice the power is produced per second; therefore, a reduction of near 50% would be required in the combination of at least one of: fuel and oxidizer, rpm, the number of cylinders or some combination therein. However, there are a whole host of effects that take this energy away such as less-than-ideal volumetric efficiency, friction, inefficient combustion, extraneous heat losses, and accelerating inertial masses. This can easily take up 75 to 85% of the power leaving only about 30 to 50 hp delivered to the rear wheels (at 60 MPH).
 
Torque and power—It is an embodiment of this instant invention that the amount of oxidizer (O 2 ) and fuel (H 2 ) admitted to the combustion chamber can be varied independently of the speed of the engine. Further, the amount of oxidizer is not limited by a fixed percentage of inert gases. Therefore, in the instant invention there is a preferred embodiment to change at least one of torque and power independent of engine speed. It is a preferred embodiment that the instant invention comprise the capability of a near vertical torque curve at a given rpm, wherein said torque curve is depicted as a function of engine rpm.
 
     Example 2 
     Utilizing a computer model developed from the information developed in Example 1, and written into an excel spreadsheet program,  FIG. 10  presents results wherein T 0 =100 K, and within each stroke the moles of H 2  range from 0.005 to 0.016 along with the moles of O 2  in a stoichiometric relationship to those of H 2 , and the moles of H 2 O vary from 0.084 to 0.252. 
     Example 3 
     Utilizing the computer model developed in Example 1, and written into an Excel spreadsheet program,  FIG. 11  presents results wherein T 0 =200 K, and within each stroke the moles of H 2  range from 0.005 to 0.016 along with the moles of O 2  in a stoichiometric relationship to those of H 2 , and the moles of H 2 O vary from 0.042 to 0.126. 
     Example 4 
     Utilizing the computer model developed in Example 1, and written into an Excel spreadsheet program,  FIG. 12  presents results wherein T 0 =300 K, and within each stroke the moles of H 2  range from 0.005 to 0.016 along with the moles of O 2  in a stoichiometric relationship to those of H 2 , and the moles of H 2 O vary from 0.028 to 0.084. 
     Example 5 
     Utilizing the computer model developed in Example 1, and written into an Excel spreadsheet program,  FIG. 13  presents results wherein T 0 =400 K, and within each stroke the moles of H 2  range from 0.005 to 0.016 along with the moles of O 2  in a stoichiometric relationship to those of H 2 , and the moles of H 2 O vary from 0.021 to 0.063. 
     Example 6 
     Utilizing the computer model developed in Example 1, and written into an Excel spreadsheet program,  FIG. 14  presents results wherein T 0 =300 K, and within each stroke the moles of H 2  range from 0.010 to 0.050 along with the moles of O 2  in a stoichiometric relationship to those of H 2 , and the moles of H 2 O vary from 0.028 to 0.084. 
     Example 7 
     Utilizing the computer model developed in Example 1, and written into an Excel spreadsheet program,  FIG. 15  presents results wherein T 0 =300 K, and within each stroke the moles of H 2  range from 0.060 to 0.100 along with the moles of O 2  in a stoichiometric relationship to those of H 2 , and the moles of H 2 O vary from 0.028 to 0.084. 
     Example 8 
     Utilizing the computer model developed in Example 1, and written into an Excel spreadsheet program,  FIG. 16  presents results wherein T 0 =300 K, and within each stroke the moles of H 2  range from 0.060 to 0.100 along with the moles of 0, in a stoichiometric relationship to those of H 2 , and the moles of H 2 O vary from 0.000 to 0.020. 
     Example 9 
     Utilizing the computer model developed in Example 1, and written into an Excel spreadsheet program,  FIG. 17  presents results wherein T 0 =300 K, and within each stroke the moles of H 2  range from 0.060 to 0.100 along with the moles of O 2  in a stoichiometric relationship to those of H 2 , and the moles of H 2 O vary from 0.100 to 0.200. 
     An additional computer model is developed for Examples 10 through 23 wherein the adiabatic expansion of steam is estimated using the adiabatic relationship: 
     
       
         
           
             W 
             = 
             
               ∫ 
               
                 P 
                 · 
                 
                    
                   V 
                 
               
             
           
         
       
       
         
           
             
               P 
               · 
               
                 V 
                 γ 
               
             
             = 
             
               
                 P 
                 0 
               
               · 
               
                 V 
                 0 
               
             
           
         
       
       
         
           
             
               W 
               = 
               
                 ∫ 
                 
                   
                     
                       
                         P 
                         0 
                       
                        
                       
                         ( 
                         
                           
                             V 
                             0 
                           
                           V 
                         
                         ) 
                       
                     
                     γ 
                   
                   · 
                   
                      
                     V 
                   
                 
               
             
             , 
             
               
 
             
              
             
               W 
               = 
               
                 
                   
                     
                       
                         P 
                         0 
                       
                       · 
                       V 
                     
                     
                       1 
                       - 
                       γ 
                     
                   
                    
                   
                     
                       ( 
                       
                         
                           V 
                           0 
                         
                         V 
                       
                       ) 
                     
                     γ 
                   
                 
                  
                 
                    
                   
                     V 
                     i 
                   
                   
                     V 
                     f 
                   
                 
               
             
           
         
       
     
     And the final temperature is estimated using the ideal gas law: 
         PV=nRT , wherein R=0.0821 (L·atm)/(mole K)
 
     In each of examples 10 through 23 a molar amount of H 2 O, as indicated, is heated to the indicated initial temperature from the heat of the combustion chamber to form steam, wherein said heat of the combustion chamber is enthalpy from the combustion of H 2  and O 2 , wherein the indicated initial temperature and the indicted initial pressure is prior to adiabatic expansion, and wherein: the work performed, the final pressure and the final temperature are after adiabatic expansion of the steam. In the instant invention it is an embodiment to add H 2 O to the combustion chamber after the combustion of H 2  and O 2  to cool the combustion chamber, wherein said H 2 O is in the form of a liquid and/or a low pressure gas at a molar ratio of about 1:0.1 to about 1:12 of H 2 :H 2 O; it is most preferred that said molar ratio be about 1:6 to about 1:10; and, it is most preferred that said molar ratio be 1:8. 
     Examples 10-13 
       
     
       
         
           
               
               
               
               
               
               
               
               
               
               
             
               
                   
               
             
            
               
                 Moles of H 2 O 
                   
                 0.08 
                 0.07 
                 0.06 
                 0.05 
                 0.04 
                 0.03 
                 0.02 
                 0.01 
               
               
                   
               
               
                 Initial Temp 
                 K 
                 500 
                 500 
                 500 
                 500 
                 500 
                 500 
                 500 
                 500 
               
               
                 Initial volume 
                 L 
                 0.07 
                 0.07 
                 0.07 
                 0.07 
                 0.07 
                 0.07 
                 0.07 
                 0.07 
               
               
                 Final volume 
                 L 
                 0.7 
                 0.7 
                 0.7 
                 0.7 
                 0.7 
                 0.7 
                 0.7 
                 0.7 
               
               
                 Initial pressure 
                 atm 
                 46.9 
                 41.1 
                 35.2 
                 29.3 
                 23.5 
                 17.6 
                 11.7 
                 5.9 
               
               
                 Work 
                 L-atm 
                 4.9 
                 4.3 
                 3.7 
                 3.1 
                 2.5 
                 1.9 
                 1.2 
                 0.6 
               
               
                 Heat 
                 cal 
                 860.4 
                 752.9 
                 645.3 
                 537.8 
                 430.2 
                 322.7 
                 215.1 
                 107.6 
               
               
                   
                 L-atm 
                 35.4 
                 31.0 
                 26.6 
                 22.1 
                 17.7 
                 13.3 
                 8.9 
                 4.4 
               
               
                 Delta T 
                 K 
                 172.1 
                 150.6 
                 129.1 
                 107.6 
                 86.0 
                 64.5 
                 43.0 
                 21.5 
               
               
                 Final pressure 
                 atm 
                 18.68 
                 16.34 
                 14.01 
                 11.67 
                 9.34 
                 7.00 
                 4.67 
                 2.33 
               
               
                 Final Temp 
                 K 
                 199 
                 199 
                 199 
                 199 
                 199 
                 199 
                 199 
                 199 
               
               
                   
               
               
                 Moles of H 2 O 
                   
                 0.08 
                 0.07 
                 0.06 
                 0.05 
                 0.04 
                 0.03 
                 0.02 
                 0.01 
               
               
                   
               
               
                 Initial Temp 
                 K 
                 773 
                 773 
                 773 
                 773 
                 773 
                 773 
                 773 
                 773 
               
               
                 Initial volume 
                 L 
                 0.07 
                 0.07 
                 0.07 
                 0.07 
                 0.07 
                 0.07 
                 0.07 
                 0.07 
               
               
                 Final volume 
                 L 
                 0.7 
                 0.7 
                 0.7 
                 0.7 
                 0.7 
                 0.7 
                 0.7 
                 0.7 
               
               
                 Initial pressure 
                 atm 
                 72.5 
                 63.5 
                 54.4 
                 45.3 
                 36.3 
                 27.2 
                 18.1 
                 9.1 
               
               
                 Work 
                 l-atm 
                 7.6 
                 6.7 
                 5.7 
                 4.8 
                 3.8 
                 2.9 
                 1.9 
                 1.0 
               
               
                 Heat 
                 cal 
                 1057.0 
                 924.8 
                 792.7 
                 660.6 
                 528.5 
                 396.4 
                 264.2 
                 132.1 
               
               
                   
                 l-atm 
                 43.5 
                 38.1 
                 32.6 
                 27.2 
                 21.7 
                 16.3 
                 10.9 
                 5.4 
               
               
                 Delta T 
                 K 
                 211.4 
                 185.0 
                 158.5 
                 132.1 
                 105.7 
                 79.3 
                 52.8 
                 26.4 
               
               
                 Final pressure 
                 atm 
                 28.87 
                 25.27 
                 21.66 
                 18.05 
                 14.44 
                 10.83 
                 7.22 
                 3.61 
               
               
                 Final Temp 
                 K 
                 308 
                 308 
                 308 
                 308 
                 308 
                 308 
                 308 
                 308 
               
               
                   
               
               
                 Moles of H 2 O 
                   
                 0.8 
                 0.7 
                 0.6 
                 0.5 
                 0.4 
                 0.3 
                 0.2 
                 0.1 
               
               
                   
               
               
                 Initial Temp 
                 K 
                 500 
                 500 
                 500 
                 500 
                 500 
                 500 
                 500 
                 500 
               
               
                 Initial volume 
                 L 
                 0.07 
                 0.14 
                 0.21 
                 0.28 
                 0.35 
                 0.42 
                 0.49 
                 0.56 
               
               
                 Final volume 
                 L 
                 0.7 
                 0.7 
                 0.7 
                 0.7 
                 0.7 
                 0.7 
                 0.7 
                 0.7 
               
               
                 Initial pressure 
                 atm 
                 469.1 
                 205.3 
                 117.3 
                 73.3 
                 46.9 
                 29.3 
                 16.8 
                 7.3 
               
               
                 Work 
                 L-atm 
                 49.4 
                 34.1 
                 23.5 
                 15.7 
                 9.9 
                 5.7 
                 2.7 
                 0.9 
               
               
                 Heat 
                 cal 
                 8604.0 
                 7528.5 
                 6453.0 
                 5377.5 
                 4302.0 
                 3226.5 
                 2151.0 
                 1075.5 
               
               
                   
                 L-atm 
                 354.1 
                 309.8 
                 265.6 
                 221.3 
                 177.0 
                 132.8 
                 88.5 
                 44.3 
               
               
                 Delta T 
                 K 
                 1720.8 
                 1505.7 
                 1290.6 
                 1075.5 
                 860.4 
                 645.3 
                 430.2 
                 215.1 
               
               
                 Final pressure 
                 atm 
                 18.68 
                 21.56 
                 21.74 
                 20.32 
                 17.78 
                 14.34 
                 10.17 
                 5.36 
               
               
                 Final Temp 
                 K 
                 199 
                 263 
                 309 
                 347 
                 379 
                 408 
                 434 
                 457 
               
               
                   
               
               
                 Moles of H 2 O 
                   
                 0.8 
                 0.7 
                 0.6 
                 0.5 
                 0.4 
                 0.3 
                 0.2 
                 0.1 
               
               
                   
               
               
                 Initial Temp 
                 K 
                 773 
                 773 
                 773 
                 773 
                 773 
                 773 
                 773 
                 773 
               
               
                 Initial volume 
                 L 
                 0.07 
                 0.14 
                 0.21 
                 0.28 
                 0.35 
                 0.42 
                 0.49 
                 0.56 
               
               
                 Final volume 
                 L 
                 0.7 
                 0.7 
                 0.7 
                 0.7 
                 0.7 
                 0.7 
                 0.7 
                 0.7 
               
               
                 Initial pressure 
                 atm 
                 725.3 
                 317.3 
                 181.3 
                 113.3 
                 72.5 
                 45.3 
                 25.9 
                 11.3 
               
               
                 Work 
                 L-atm 
                 76.4 
                 52.7 
                 36.4 
                 24.3 
                 15.4 
                 8.8 
                 4.2 
                 1.4 
               
               
                 Heat 
                 Cal 
                 10569.6 
                 9248.4 
                 7927.2 
                 6606.0 
                 5284.8 
                 3963.6 
                 2642.4 
                 1321.2 
               
               
                   
                 L-atm 
                 435.0 
                 380.6 
                 326.2 
                 271.9 
                 217.5 
                 163.1 
                 108.7 
                 54.4 
               
               
                 Delta T 
                 K 
                 2113.9 
                 1849.7 
                 1585.4 
                 1321.2 
                 1057.0 
                 792.7 
                 528.5 
                 264.2 
               
               
                 Final pressure 
                 atm 
                 28.87 
                 33.34 
                 33.61 
                 31.42 
                 27.48 
                 22.17 
                 15.72 
                 8.29 
               
               
                 Final Temp 
                 K 
                 308 
                 406 
                 478 
                 536 
                 586 
                 630 
                 670 
                 707 
               
               
                   
               
            
           
         
       
     
     Examples 14-17 
       
     
       
         
           
               
               
               
               
               
               
               
               
               
               
             
               
                   
               
             
            
               
                 Moles of H 2 O 
                   
                 0.08 
                 0.08 
                 0.06 
                 0.05 
                 0.04 
                 0.03 
                 0.02 
                 0.01 
               
               
                   
               
               
                 Initial Temp 
                 K 
                 773 
                 773 
                 773 
                 773 
                 773 
                 773 
                 773 
                 773 
               
               
                 Initial volume 
                 L 
                 0.07 
                 0.07 
                 0.07 
                 0.07 
                 0.07 
                 0.07 
                 0.07 
                 0.07 
               
               
                 Final volume 
                 L 
                 0.9 
                 0.9 
                 0.9 
                 0.9 
                 0.9 
                 0.9 
                 0.9 
                 0.9 
               
               
                 Initial pressure 
                 atm 
                 72.5 
                 72.5 
                 54.4 
                 45.3 
                 36.3 
                 27.2 
                 18.1 
                 9.1 
               
               
                 Work 
                 L-atm 
                 8.1 
                 8.1 
                 6.1 
                 5.1 
                 4.1 
                 3.0 
                 2.0 
                 1.0 
               
               
                 Heat 
                 cal 
                 1057.0 
                 1057.0 
                 792.7 
                 660.6 
                 528.5 
                 396.4 
                 264.2 
                 132.1 
               
               
                   
                 L-atm 
                 43.5 
                 43.5 
                 32.6 
                 27.2 
                 21.7 
                 16.3 
                 10.9 
                 5.4 
               
               
                 Delta T 
                 K 
                 211.4 
                 211.4 
                 158.5 
                 132.1 
                 105.7 
                 79.3 
                 52.8 
                 26.4 
               
               
                 Final pressure 
                 atm 
                 2.03 
                 2.03 
                 1.52 
                 1.27 
                 1.02 
                 0.76 
                 0.51 
                 0.25 
               
               
                 Final Temp 
                 K 
                 278 
                 278 
                 278 
                 278 
                 278 
                 278 
                 278 
                 278 
               
               
                   
               
               
                 Moles of H 2 O 
                   
                 0.8 
                 0.7 
                 0.6 
                 0.5 
                 0.4 
                 0.3 
                 0.2 
                 0.1 
               
               
                   
               
               
                 Initial Temp 
                 K 
                 773 
                 773 
                 773 
                 773 
                 773 
                 773 
                 773 
                 773 
               
               
                 Initial volume 
                 L 
                 0.07 
                 0.07 
                 0.07 
                 0.07 
                 0.07 
                 0.07 
                 0.07 
                 0.07 
               
               
                 Final volume 
                 L 
                 0.9 
                 0.9 
                 0.9 
                 0.9 
                 0.9 
                 0.9 
                 0.9 
                 0.9 
               
               
                 Initial pressure 
                 atm 
                 725.3 
                 634.6 
                 544.0 
                 453.3 
                 362.6 
                 272.0 
                 181.3 
                 90.7 
               
               
                 Work 
                 L-atm 
                 81.2 
                 71.1 
                 60.9 
                 50.8 
                 40.6 
                 30.5 
                 20.3 
                 10.2 
               
               
                 Heat 
                 cal 
                 10569.6 
                 9248.4 
                 7927.2 
                 6606.0 
                 5284.8 
                 3963.6 
                 2642.4 
                 1321.2 
               
               
                   
                 L-atm 
                 435.0 
                 380.6 
                 326.2 
                 271.9 
                 217.5 
                 163.1 
                 108.7 
                 54.4 
               
               
                 Delta T 
                 K 
                 2113.9 
                 1849.7 
                 1585.4 
                 1321.2 
                 1057.0 
                 792.7 
                 528.5 
                 264.2 
               
               
                 Final pressure 
                 atm 
                 20.31 
                 17.77 
                 15.23 
                 12.69 
                 10.16 
                 7.62 
                 5.08 
                 2.54 
               
               
                 Final temp 
                 K 
                 278 
                 278 
                 278 
                 278 
                 278 
                 278 
                 278 
                 278 
               
               
                   
               
               
                 Moles of H 2 O 
                   
                 0.08 
                 0.08 
                 0.06 
                 0.05 
                 0.04 
                 0.03 
                 0.02 
                 0.01 
               
               
                   
               
               
                 Initial Temp 
                 K 
                 773 
                 773 
                 773 
                 773 
                 773 
                 773 
                 773 
                 773 
               
               
                 Initial volume 
                 L 
                 0.35 
                 0.35 
                 0.35 
                 0.35 
                 0.35 
                 0.35 
                 0.35 
                 0.35 
               
               
                 Final volume 
                 L 
                 0.7 
                 0.7 
                 0.7 
                 0.7 
                 0.7 
                 0.7 
                 0.7 
                 0.7 
               
               
                 Initial pressure 
                 atm 
                 14.5 
                 14.5 
                 10.9 
                 9.1 
                 7.3 
                 5.4 
                 3.6 
                 1.8 
               
               
                 Work 
                 L-atm 
                 3.1 
                 3.1 
                 2.3 
                 1.9 
                 1.5 
                 1.2 
                 0.8 
                 0.4 
               
               
                 Heat 
                 cal 
                 1057.0 
                 1057.0 
                 792.7 
                 660.6 
                 528.5 
                 396.4 
                 264.2 
                 132.1 
               
               
                   
                 L-atm 
                 43.5 
                 43.5 
                 32.6 
                 27.2 
                 21.7 
                 16.3 
                 10.9 
                 5.4 
               
               
                 Delta T 
                 K 
                 211.4 
                 211.4 
                 158.5 
                 132.1 
                 105.7 
                 79.3 
                 52.8 
                 26.4 
               
               
                 Final pressure 
                 atm 
                 5.50 
                 5.50 
                 4.12 
                 3.44 
                 2.75 
                 2.06 
                 1.37 
                 0.69 
               
               
                 Final Temp 
                 K 
                 586 
                 586 
                 586 
                 586 
                 586 
                 586 
                 586 
                 586 
               
               
                   
               
               
                 Moles of H 2 O 
                   
                 0.8 
                 0.7 
                 0.6 
                 0.5 
                 0.4 
                 0.3 
                 0.2 
                 0.1 
               
               
                   
               
               
                 Initial Temp 
                 K 
                 773 
                 773 
                 773 
                 773 
                 773 
                 773 
                 773 
                 773 
               
               
                 Initial volume 
                 L 
                 0.35 
                 0.35 
                 0.35 
                 0.35 
                 0.35 
                 0.35 
                 0.35 
                 0.35 
               
               
                 Final volume 
                 L 
                 0.7 
                 0.7 
                 0.7 
                 0.7 
                 0.7 
                 0.7 
                 0.7 
                 0.7 
               
               
                 Initial pressure 
                 atm 
                 145.1 
                 126.9 
                 108.8 
                 90.7 
                 72.5 
                 54.4 
                 36.3 
                 18.1 
               
               
                 Work 
                 L-atm 
                 30.7 
                 26.9 
                 23.1 
                 19.2 
                 15.4 
                 11.5 
                 7.7 
                 3.8 
               
               
                 Heat 
                 cal 
                 10569.6 
                 9248.4 
                 7927.2 
                 6606.0 
                 5284.8 
                 3963.6 
                 2642.4 
                 1321.2 
               
               
                   
                 L-atm 
                 435.0 
                 380.6 
                 326.2 
                 271.9 
                 217.5 
                 163.1 
                 108.7 
                 54.4 
               
               
                 Delta T 
                 K 
                 2113.9 
                 1849.7 
                 1585.4 
                 1321.2 
                 1057.0 
                 792.7 
                 528.5 
                 264.2 
               
               
                 Final pressure 
                 atm 
                 54.97 
                 48.10 
                 41.23 
                 34.35 
                 27.48 
                 20.61 
                 13.74 
                 6.87 
               
               
                 Final Temp 
                 K 
                 586 
                 586 
                 586 
                 586 
                 586 
                 586 
                 586 
                 586 
               
               
                   
               
            
           
         
       
     
     Examples 18-21 
       
     
       
         
           
               
               
               
               
               
               
               
               
               
               
             
               
                   
               
             
            
               
                 Moles of H 2 O 
                   
                 0.08 
                 0.08 
                 0.06 
                 0.05 
                 0.04 
                 0.03 
                 0.02 
                 0.01 
               
               
                   
               
               
                 Initial Temp 
                 K 
                 1000 
                 1000 
                 1000 
                 1000 
                 1000 
                 1000 
                 1000 
                 1000 
               
               
                 Initial volume 
                 L 
                 0.07 
                 0.07 
                 0.07 
                 0.07 
                 0.07 
                 0.07 
                 0.07 
                 0.07 
               
               
                 Final volume 
                 L 
                 1.4 
                 1.4 
                 1.4 
                 1.4 
                 1.4 
                 1.4 
                 1.4 
                 1.4 
               
               
                 Initial pressure 
                 atm 
                 93.8 
                 93.8 
                 70.4 
                 58.6 
                 46.9 
                 35.2 
                 23.5 
                 11.7 
               
               
                 Work 
                 L-atm 
                 11.5 
                 11.5 
                 8.6 
                 7.2 
                 5.7 
                 4.3 
                 2.9 
                 1.4 
               
               
                 Heat 
                 cal 
                 1220.4 
                 1220.4 
                 915.3 
                 762.8 
                 610.2 
                 457.7 
                 305.1 
                 152.6 
               
               
                   
                 L-atm 
                 50.2 
                 50.2 
                 37.7 
                 31.4 
                 25.1 
                 18.8 
                 12.6 
                 6.3 
               
               
                 Delta T 
                 K 
                 244.1 
                 244.1 
                 183.1 
                 152.6 
                 122.0 
                 91.5 
                 61.0 
                 30.5 
               
               
                 Final pressure 
                 atm 
                 1.42 
                 1.42 
                 1.06 
                 0.88 
                 0.71 
                 0.53 
                 0.35 
                 0.18 
               
               
                 Final temp 
                 K 
                 302 
                 302 
                 302 
                 302 
                 302 
                 302 
                 302 
                 302 
               
               
                   
               
               
                 Moles of H 2 O 
                   
                 0.8 
                 0.7 
                 0.6 
                 0.5 
                 0.4 
                 0.3 
                 0.2 
                 0.1 
               
               
                   
               
               
                 Initial Temp 
                 K 
                 1000 
                 1000 
                 1000 
                 1000 
                 1000 
                 1000 
                 1000 
                 1000 
               
               
                 Initial volume 
                 L 
                 0.07 
                 0.07 
                 0.07 
                 0.07 
                 0.07 
                 0.07 
                 0.07 
                 0.07 
               
               
                 Final volume 
                 L 
                 1.7 
                 1.7 
                 1.7 
                 1.7 
                 1.7 
                 1.7 
                 1.7 
                 1.7 
               
               
                 Initial pressure 
                 atm 
                 938.3 
                 821.0 
                 703.7 
                 586.4 
                 469.1 
                 351.9 
                 234.6 
                 117.3 
               
               
                 Work 
                 L-atm 
                 118.4 
                 103.6 
                 88.8 
                 74.0 
                 59.2 
                 44.4 
                 29.6 
                 14.8 
               
               
                 Heat 
                 cal 
                 12204.0 
                 10678.5 
                 9153.0 
                 7627.5 
                 6102.0 
                 4576.5 
                 3051.0 
                 1525.5 
               
               
                   
                 L-atm 
                 502.2 
                 439.4 
                 376.7 
                 313.9 
                 251.1 
                 188.3 
                 125.6 
                 62.8 
               
               
                 Delta T 
                 K 
                 2440.8 
                 2135.7 
                 1830.6 
                 1525.5 
                 1220.4 
                 915.3 
                 610.2 
                 305.1 
               
               
                 Final pressure 
                 atm 
                 10.79 
                 9.44 
                 8.09 
                 6.74 
                 5.39 
                 4.04 
                 2.70 
                 1.35 
               
               
                 Final Temp 
                 K 
                 279 
                 279 
                 279 
                 279 
                 279 
                 279 
                 279 
                 279 
               
               
                   
               
               
                 Moles of H 2 O 
                   
                 0.08 
                 0.08 
                 0.06 
                 0.05 
                 0.04 
                 0.03 
                 0.02 
                 0.01 
               
               
                   
               
               
                 Initial Temp 
                 K 
                 2000 
                 2000 
                 2000 
                 2000 
                 2000 
                 2000 
                 2000 
                 2000 
               
               
                 Initial volume 
                 L 
                 0.07 
                 0.07 
                 0.07 
                 0.07 
                 0.07 
                 0.07 
                 0.07 
                 0.07 
               
               
                 Final volume 
                 L 
                 9.8 
                 9.8 
                 9.8 
                 9.8 
                 9.8 
                 9.8 
                 9.8 
                 9.8 
               
               
                 Initial pressure 
                 atm 
                 187.7 
                 187.7 
                 140.7 
                 117.3 
                 93.8 
                 70.4 
                 46.9 
                 23.5 
               
               
                 Work 
                 L-atm 
                 28.3 
                 28.3 
                 21.2 
                 17.7 
                 14.1 
                 10.6 
                 7.1 
                 3.5 
               
               
                 Heat 
                 cal 
                 1940.4 
                 1940.4 
                 1455.3 
                 1212.8 
                 970.2 
                 727.7 
                 485.1 
                 242.6 
               
               
                   
                 L-atm 
                 79.9 
                 79.9 
                 59.9 
                 49.9 
                 39.9 
                 29.9 
                 20.0 
                 10.0 
               
               
                 Delta T 
                 K 
                 388.1 
                 388.1 
                 291.1 
                 242.6 
                 194.0 
                 145.5 
                 97.0 
                 48.5 
               
               
                 Final pressure 
                 Atm 
                 0.19 
                 0.19 
                 0.14 
                 0.12 
                 0.09 
                 0.07 
                 0.05 
                 0.02 
               
               
                 Final temp 
                 K 
                 277 
                 277 
                 277 
                 277 
                 277 
                 277 
                 277 
                 277 
               
               
                   
               
               
                 Moles of H 2 O 
                   
                 0.8 
                 0.7 
                 0.6 
                 0.5 
                 0.4 
                 0.3 
                 0.2 
                 0.1 
               
               
                   
               
               
                 Initial Temp 
                 K 
                 2000 
                 2000 
                 2000 
                 2000 
                 2000 
                 2000 
                 2000 
                 2000 
               
               
                 Initial volume 
                 L 
                 0.07 
                 0.07 
                 0.07 
                 0.07 
                 0.07 
                 0.07 
                 0.07 
                 0.07 
               
               
                 Final volume 
                 L 
                 9.8 
                 9.8 
                 9.8 
                 9.8 
                 9.8 
                 9.8 
                 9.8 
                 9.8 
               
               
                 Initial pressure 
                 atm 
                 1876.6 
                 1642.0 
                 1407.4 
                 1172.9 
                 938.3 
                 703.7 
                 469.1 
                 234.6 
               
               
                 Work 
                 L-atm 
                 282.9 
                 247.5 
                 212.2 
                 176.8 
                 141.5 
                 106.1 
                 70.7 
                 35.4 
               
               
                 Heat 
                 cal 
                 19404.0 
                 16978.5 
                 14553.0 
                 12127.5 
                 9702.0 
                 7276.5 
                 4851.0 
                 2425.5 
               
               
                   
                 L-atm 
                 798.5 
                 698.7 
                 598.9 
                 499.1 
                 399.3 
                 299.4 
                 199.6 
                 99.8 
               
               
                 Delta T 
                 K 
                 3880.8 
                 3395.7 
                 2910.6 
                 2425.5 
                 1940.4 
                 1455.3 
                 970.2 
                 485.1 
               
               
                 Final pressure 
                 atm 
                 1.86 
                 1.62 
                 1.39 
                 1.16 
                 0.93 
                 0.70 
                 0.46 
                 0.23 
               
               
                 Final temp 
                 K 
                 277 
                 277 
                 277 
                 277 
                 277 
                 277 
                 277 
                 277 
               
               
                   
               
            
           
         
       
     
     Examples 22-23 
       
     
       
         
           
               
               
               
               
               
               
               
               
               
               
             
               
                   
               
             
            
               
                 Moles of H 2 O 
                   
                 0.08 
                 0.08 
                 0.06 
                 0.05 
                 0.04 
                 0.03 
                 0.02 
                 0.01 
               
               
                   
               
               
                 Initial Temp 
                 K 
                 400 
                 400 
                 400 
                 400 
                 400 
                 400 
                 400 
                 400 
               
               
                 Initial volume 
                 L 
                 0.3 
                 0.3 
                 0.3 
                 0.3 
                 0.3 
                 0.3 
                 0.3 
                 0.3 
               
               
                 Final volume 
                 L 
                 0.7 
                 0.7 
                 0.7 
                 0.7 
                 0.7 
                 0.7 
                 0.7 
                 0.7 
               
               
                 Initial pressure 
                 atm 
                 8.8 
                 8.8 
                 6.6 
                 5.5 
                 4.4 
                 3.3 
                 2.2 
                 1.1 
               
               
                 Work 
                 L-atm 
                 1.9 
                 1.9 
                 1.4 
                 1.2 
                 0.9 
                 0.7 
                 0.5 
                 0.2 
               
               
                 Heat 
                 cal 
                 788.4 
                 788.4 
                 591.3 
                 492.8 
                 394.2 
                 295.7 
                 197.1 
                 98.6 
               
               
                   
                 L-atm 
                 32.4 
                 32.4 
                 24.3 
                 20.3 
                 16.2 
                 12.2 
                 8.1 
                 4.1 
               
               
                 Delta T 
                 K 
                 157.7 
                 157.7 
                 118.3 
                 98.6 
                 78.8 
                 59.1 
                 39.4 
                 19.7 
               
               
                 Final pressure 
                 atm 
                 2.67 
                 2.67 
                 2.01 
                 1.67 
                 1.34 
                 1.00 
                 0.67 
                 0.33 
               
               
                 Final temp 
                 K 
                 285 
                 285 
                 285 
                 285 
                 285 
                 285 
                 285 
                 285 
               
               
                   
               
               
                 Moles of H 2 O 
                   
                 0.8 
                 0.7 
                 0.6 
                 0.5 
                 0.4 
                 0.3 
                 0.2 
                 0.1 
               
               
                   
               
               
                 Initial Temp 
                 K 
                 400 
                 400 
                 400 
                 400 
                 400 
                 400 
                 400 
                 400 
               
               
                 Initial volume 
                 L 
                 0.3 
                 0.3 
                 0.3 
                 0.3 
                 0.3 
                 0.3 
                 0.3 
                 0.3 
               
               
                 Final volume 
                 L 
                 0.7 
                 0.7 
                 0.7 
                 0.7 
                 0.7 
                 0.7 
                 0.7 
                 0.7 
               
               
                 Initial pressure 
                 atm 
                 87.6 
                 76.6 
                 65.7 
                 54.7 
                 43.8 
                 32.8 
                 21.9 
                 10.9 
               
               
                 Work 
                 L-atm 
                 18.9 
                 16.5 
                 14.2 
                 11.8 
                 9.4 
                 7.1 
                 4.7 
                 2.4 
               
               
                 Heat 
                 cal 
                 7884.0 
                 6898.5 
                 5913.0 
                 4927.5 
                 3942.0 
                 2956.5 
                 1971.0 
                 985.5 
               
               
                   
                 L-atm 
                 324.4 
                 283.9 
                 243.3 
                 202.8 
                 162.2 
                 121.7 
                 81.1 
                 40.6 
               
               
                 Delta T 
                 K 
                 1576.8 
                 1379.7 
                 1182.6 
                 985.5 
                 788.4 
                 591.3 
                 394.2 
                 197.1 
               
               
                 Final pressure 
                 atm 
                 26.74 
                 23.40 
                 20.06 
                 16.71 
                 13.37 
                 10.03 
                 6.69 
                 3.34 
               
               
                 Final temp 
                 K 
                 285 
                 285 
                 285 
                 285 
                 285 
                 285 
                 285 
                 285 
               
               
                   
               
            
           
         
       
     
     Certain objects are set forth above and made apparent from the foregoing description. However, since certain changes may be made in the above description without departing from the scope of the invention, it is intended that all matters contained in the foregoing description shall be interpreted as illustrative only of the principles of the invention and not in a limiting sense. With respect to the above description, it is to be realized that any descriptions, drawings and examples deemed readily apparent and obvious to one skilled in the art and all equivalent relationships to those described in the specification are intended to be encompassed by the present invention. 
     Further, since numerous modifications and changes will readily occur to those skilled in the art, it is not desired to limit the invention to the exact construction and operation shown and described, and accordingly, all suitable modifications and equivalents may be resorted to, falling within the scope of the invention, It is also to be understood that the following claims are intended to cover all of the generic and specific features of the invention herein described, and all statements of the scope of the invention, which, as a matter of language, might be said to fall in between.