Patent Abstract:
A quantum jet turbine propulsion system includes a plurality of jet turbine engines housed within an airtight common exhaust system. The individual jet turbine engines receive propulsion from fuel and air sources remote from the engines, preferably provided by fuel and air pumps and air compressors. The jet turbine propulsion system includes its own turbine driven generator as a self-generating power source, and achieves increased efficiencies through the use of a specially adapted exhaust housing configuration. The jet turbine propulsion system is suitable for use in all forms of land, sea, air and space vehicles. Although many propulsion sources can be used, a preferred propulsion source is a mixture of water and air.

Full Description:
BACKGROUND OF THE INVENTION  
       [0001]     1. Field of Invention  
         [0002]     This invention relates to a modified jet engine for use in various land vehicles, sea craft, or flying craft that is housed within a sealed exhaust system and augmented by powerful compressors and air and fuel pumps to deliver oxygen and fuel needs to achieve improved energy efficiency, fuel economy, safety and versatility.  
         [0003]     2. Description of Related Art  
         [0004]     Numerous land vehicles, flying craft and sea craft utilize solid, gas or liquid fossil fuels in jet or rocket engines to provide thrust for propulsion of the craft/vehicle. While many improvements have been made over the years, the main focus in further efficiency has been in the engine design, with much energy still being wasted or needlessly expelled out of the exhaust of such conventional engine exhaust systems.  
         [0005]     There is a need for an efficient, economical, safe and versatile jet or rocket engine that can minimize wasted fuel.  
         [0006]     Other problems with conventional jet engines are the conventional requirement for an open-mouth intake system in which incoming air enters the jet directly from the atmosphere. Occasionally, objects are sucked into such jet engines where they can damage or completely render inoperable several components of the jet engine. As such, there is a need for an improved jet turbine system that locates an air source remote from the jet turbine itself.  
         [0007]     There also is a need for a jet turbine system that can operate using a multitude of different fuel sources, particularly environmentally friendly sources such as air and water.  
       SUMMARY OF THE INVENTION  
       [0008]     Applicant has overcome various long felt needs by providing a novel quantum jet turbine system that is housed within an airtight exhaust system. One or more jet turbine engines can share one common exhaust system depending on the size and design of the fuselage and its application. This sealed type quantum jet engine puts to an end the numerous problems associated with conventional jet engine design, since by having the quantum jet engine sealed and housed within one exhaust system, the engine can prevent entry of foreign objects. With this design, independent fuel and compressed air supplies are fed to the sealed jet turbines through sealed feed lines. Moreover, by elimination of an integral open atmosphere intake, the jet is readily adaptable to rocket use for space travel when coupled with a self-contained source of oxygen, such as a liquid or compressed oxygen or air storage tank. Thus, a craft with a quantum jet turbine can fly or land anywhere, including in the presence of flocks of birds, insects, mammals, or dust, while keeping out such foreign objects. Moreover, the system is adaptable to atmospheric, stratospheric or space flight.  
         [0009]     By coupling a turbine of the jet to a generator, thrust generated by the jet can be used to generate electricity to power the electrical needs of the jet engine and the craft.  
         [0010]     By coupling the sealed quantum jet turbine to a compound exhaust system, further efficiencies are achieved by minimizing wasted fuel. That is, conventional jet and rocket engines operate by burning and directly expelling huge amounts of accelerated and expanded gases from their exhaust tubes instantly into the atmosphere, where they can do no further kinetic work. However, when coupled with an efficient exhaust system that harnesses such gases, further efficient use of the kinetic potential of the expelled gases can be realized. This reduces fuel consumption, which in turn reduces payloads by reducing the quantities of fuel needed to be stored, which also itself increases efficiencies since less mass is being propelled. A preferred compound exhaust system can be found in Applicant&#39;s U.S. Pat. No. 6,367,739, the subject matter of which is hereby incorporated herein by reference in its entirety.  
         [0011]     Thus, whereas conventional jet and rocket engines expend about 50% or more of the volume of burnt fuels into the atmosphere with no potential to do further kinetic work, the inventive quantum jet engines, when combined with a compound exhaust, are capable of greater potential efficiency by causing the expanding gases to pass through several additional gas expansion chambers, thereby using more of the available kinetic forces from the combusting gases.  
         [0012]     Also, while conventional rockets expel huge amounts of burnt gases at a rather low exit speed, the inventive quantum jet turbine produces kinetic energy for propulsion by expelling the gases at a much lower volume, but at a much higher velocity. Because the kinetic energy in a moving body depends on the square of its speed, it follows that harnessing ultra high speed gas molecules in a small volume and repeating the expansions through several exhaust chambers will result in a highly efficient design capable of reduced fuel consumption and comparable thrust output.  
         [0013]     Moreover, this design incorporates quantum theory by being able to radiate energy discontinuously in quanta.  
         [0014]     This sealed configuration also greatly reduces engine noise. Further noise reduction can be attained by use of a noise canceling device installed in the tip of the thrust vector nozzle of the exhaust.  
         [0015]     The inventive quantum jet turbine should highly revolutionize the air and space transportation system by introducing new fuselage designs, other than conventional tubular craft, that are more adaptable and efficient in using the modified sealed jet engine designs. Such new engines are suitable for land, sea and aircraft needs, as well as spacecraft. For example, the sealed quantum jet engines which can operate without an open-mouth intake design are particularly suitable for saucer-shaped craft, such as disclosed in Applicant&#39;s U.S. Pat. No. 6,290,184, the subject matter of which is hereby incorporated herein by reference in its entirety. Such engines may also be used to power land vehicles, such as cars, trucks, vans, commercial trucks, sports cars, race cars, etc. One suitable application of such a land vehicle can be found in Applicant&#39;s co-pending U.S. application Ser. No. ______ (Attorney Docket No. 102902), the subject matter of which is hereby incorporated herein by reference in its entirety. One suitable application of such a space craft can be found in Applicant&#39;s co-pending U.S. application Ser. No. ______ (Attorney Docket No. 104148), the subject matter of which is hereby incorporated herein by reference in its entirety.  
         [0016]     The inventive quantum jet turbine is also extremely versatile and adaptable to a multitude of possible fuel sources, such as high grade kerosene, high grade diesel fuel, alcohol, liquid hydrogen, liquid oxygen, methane, or other liquid or solid fossil fuels. It can also operate on a mixture, such as a 70/30 mix of high grade (distilled) alcohol (C2H6O), C2H50H, or CH3OH) plus distilled purified water (H 2 O), which results in an efficient, safe and more environmentally friendly fuel that can be smokeless. Other applications may use a 50/50 mixture of alcohol and water, or may use 100% purified water alone (or with superchilled air) as a steam-powered version or a superchilled air version, that are completely environmentally friendly solutions that do not rely on fossil fuels. 
     
    
     BRIEF DESCRIPTION OF THE DRAWINGS  
       [0017]     The invention will be described with reference to the following drawings wherein:  
         [0018]      FIG. 1  shows a cross-sectional view of an exemplary dual quantum jet turbine engine system housed in a common exhaust system according to the invention with various components only schematically represented;  
         [0019]      FIG. 2  shows a cross-sectional view of a second exemplary embodiment of a dual quantum jet turbine engine system housed in a common exhaust system according to the invention with various components only schematically represented;  
         [0020]      FIG. 3  shows an alternative embodiment of a dual quantum jet turbine engine system having an external turbine generator according to the invention;  
         [0021]      FIG. 4  shows a further alternative embodiment of a dual quantum jet turbine engine system having an external turbine generator according to the invention; and  
         [0022]      FIG. 5  shows an exemplary flying craft within which the inventive quantum jet turbine engine system can be effectively used. 
     
    
     DETAILED DESCRIPTION OF PREFERRED EMBODIMENTS  
       [0023]     An exemplary embodiment of the invention will be described with reference to  FIG. 1 , which shows dual quantum jet turbine engines housed in a common air-tight sealed exhaust system. The jet engines do not take in air directly from the atmosphere as in conventional jet engines. Rather, air or oxygen are received through sealed feed lines from efficient and independent on-board air compressors on the craft or externally provided for the engines. The air compressors may receive and transfer to the quantum jet engines air/oxygen received from either a remote storage tank or a remote air intake separate from the sealed jet turbine engines. The incoming air may be filtered as desired. The incoming air may also be chilled before being pumped into the jet engines. This puts an end to the numerous problems associated with conventional jet engine designs that are prone to sucking large objects into their jet engine intakes.  
         [0024]     Although shown as a dual engine model, the quantum jet turbine system according to exemplary embodiments of the invention can come in mono, dual, tri, quad or more jet engines commonly housed in a single air-tight sealed exhaust system. However, additional advantages are realized when more than one jet engine is provided within each exhaust system. The jet engines are suitably sized and symmetrically arranged within the exhaust system as shown, so as to provide a commonly and centrally oriented gas exhaust flow path.  
         [0025]     In particular,  FIG. 1  shows a quantum jet turbine system  100  including multiple separate quantum jet engines  200  housed within a single, common sealed exhaust system, preferably made up of sections A 1 , B 1 , C 1 , D 1  and E 1 . Each quantum jet engine  200  is housed in section A 1  of the exhaust system and includes an outer casing  210  having a sealed, airtight top and converging lower walls  220  defining a combustion chamber  230  therebetween. Each quantum jet engine  200  further includes a combustion exit orifice  240 .  
         [0026]     Within each combustion chamber  230  are located one or more air nozzles  250 . Air nozzles  250  are operably connected to an electric air compressor  1030  through a suitable airtight, sealed feed line (unshown) sized to match the particular jet engine used. Flow from the compressor  1030  to air nozzles  250  may be enhanced by air pump  1020  provided in-line between compressor  1030  and air nozzles  250 . Electric air compressors  1030  may receive air/oxygen from a suitable remote source, such as an on-board storage tank or through shown intake  1060 , which is in communication with the atmosphere, but provided remote from the jet engines  200 . Suitable filtering may be provided at or between the intake  1060  and electric compressors  1030  to prevent large objects from entering the system. For example, in an exemplary embodiment, air valves are located outside the fuselage of the craft on which the jet engines are installed. Air filters may be provided at the tips of the valves. The incoming air is drawn into efficient compressors  1030 , which may house their own filters. Incoming air is then fed through air tubes into a chilling mechanism  1050 , where the chilled air is then pumped into combustion chamber  230 . As shown, the chilling mechanism  1050 , air compressors  1030 , air pumps  1020 , and air intake  1060  are located around the periphery of the jet engine, external of the sealed exhaust system.  
         [0027]     Also within each combustion chamber  230  are located one or more fuel nozzles  260 . Fuel nozzles  260  are operably connected to an on-board fuel storage tank  1070  through a suitable airtight, sealed feedline (unshown). Flow from the tank  1070  may be enhanced by a fuel pump  1010  provided in-line between the tank  1070  and fuel nozzles  260 .  
         [0028]     A spark generator  270  is also provided within the combustion chamber  230  ofeachjet engine  200 . Spark generators  270  may receive electrical power from one or more on-board batteries  1040 , or from generator  400  provided within the common exhaust system. Generator  400  may be operably connected through a shaft or other structure to a turbine  300  having one or more turbine blades placed in the exit path of the combustion exit orifices  240  as shown. Upon generation of combustion gases exiting the various jet engines  200  through orifices  240 , rotation of turbine  300  will occur, which can be used with known and conventional structure to generate electrical energy from generator  400 . Electrical output from generator  400  may be electrically connected to batteries  1040  for recharging purposes and/or may be used to power various auxiliary devices, such as processor  1000 , fuel pump  1010 , air pump  1020 , electric air compressors  1030 , cooling mechanisms  1050  or other devices associated with the engine or craft.  
         [0029]     During operation, quantum jet turbine engines  200  are started by activating battery power to both the air and fuel pumps  1020 ,  1010 , respectively. Upon reaching suitable operating pressures, a desired amount of air and fuel will be fed to combustion chambers  230  while spark generators  270  are electrically activated. Upon initial ignition, processor  1000  can cut off battery current and simultaneously activate the main electric air compressors  1030 , while simultaneously activating the fuel and air pumps and other electrical devices by way of current flowing from generator  400 , which is suitably sized to power all required electrical devices.  
         [0030]     The inventive quantum jet turbine system is extremely versatile and adaptable to a multitude of possible fuel sources, such as high grade kerosene, high grade diesel fuel, alcohol, liquid hydrogen, liquid oxygen, methanol, or other solid or liquid fossil fuels. It can also operate on a mixture, such as a 70/30 mix of high grade (distilled) alcohol (C2H6O, C2H50H, or CH3OH) plus distilled purified water (H 2 O), which results in an efficient, safe and more environmentally friendly fuel that can be smokeless. Other applications may use a 50/50 mixture of alcohol and water. However, a most environmentally friendly solution would use 100% purified water alone or with superchilled air as a steam-powered version or a superchilled air version that does not rely on fossil fuels.  
         [0031]     In the exemplary embodiment of  FIG. 1 , a possible fuel mix of 70% high grade alcohol (C2H6O) plus 30% distilled water (H 2 O) is used, considering the physical properties of both compounds wherein alcohol has a low boiling point of about 375° F. (197.2° C.) and distilled water has a boiling point of 212° F. (100° C.). Both compounds should be distilled to make them more efficient in achieving faster conversion from liquid to gaseous state, due to the pure substances having no other minerals or deposits that are not combustible and could solidify and produce nozzle clogging or contamination to the combustion chamber walls  210 , which can cause maintenance problems.  
         [0032]     Most alcohols and water mix well. As such, the combination is suitable as a mixture. When this fuel mix is fed to the combustion chambers  230  and ignited by spark generators  270 , the alcohol portion of the mix burns easily, raising the temperature inside the combustion chambers  230  to over 100° C. in a very short time. Thus, expanded gases from the burnt alcohol will start moving at extreme speeds. Likewise, the water portion of the mix (30%) will be rapidly heated and boiled into steam at 100° C., at which time it also expands and moves at great speeds through the combustion chambers  230  towards exit orifices  240 , where the accelerating and expanding gases pass across turbine  300 . This generates electrical power from generator  400  used to continue operation of all electrical accessories.  
         [0033]     The exiting combustion gases enter an upper gas reaction area  510  formed from converging walls  500  of exhaust section B 1 . In this section, the exiting gases further expand and develop high pressure and temperature, ever continuously expanding and rushing toward automatic adjustable gas entry point  520  where the exiting gases then enter a lower gas reaction area  620  formed by diverging walls  600  of exhaust section C 1 . In lower gas reaction area  620 , the exiting gases further increase in pressure and temperature and enter the first stage of a multiple stage compound exhaust system  700  provided at section D 1  of the exhaust system. As shown, there are three stages formed by stage sections  710 ,  720  and  730 . Continued flow paths of the exiting gases develop multiple action and reaction forces, acting to further extract kinetic force from the gases and further providing thrust force to propel the jet and associated craft upward. A suitable exemplary multiple stage compound exhaust system is the 3-stage compound exhaust system disclosed in U.S. Pat. No. 6,367,739, the subject matter of which is hereby incorporated herein by reference in its entirety. However, advantages can be achieved by as few as two stages and as many as 10 or more, the higher the number the higher the efficiency.  
         [0034]     The compound exhaust system works by careful control of the kinetic forces acting on the exhaust gases. The gas molecules traveling from the combustion chambers into the first stage of the compound exhaust system at a high speed become abruptly stopped at the top surface of the first stage of the exhaust, where it is known from conservation of energy that the kinetic energy becomes transferred into heat. At this time, the orderly motion of the high speed molecules becomes chaotic, and in an instant the molecules again regroup and move upward, pushing the incoming gases up by reactionary forces. Upon being pushed back by stronger gases coming from the exhaust, the gas molecules further regroup and exit toward the high speed jet nozzles of the exhaust system into the second stage of the exhaust system, where the movement pattern is repeated until the gases reach the third stage where the movement is repeated a third time until the gases finally exit the exhaust chamber.  
         [0035]     Upon exiting from compound exhaust system  700 , exiting combustion gases are received by thrust vector nozzle  800 , which can be suitably controlled to direct the exiting gases in a desired thrust vector that may be other than in axial alignment with the exhaust system. Owing to the sealed intake structure, such a jet engine will operate with reduced sound level than that typically found on conventional jet engines that include a large open-mouth intake system. If additional sound reducing properties are desired, a conventional sound cancellation device  900  can be installed to the end of the exhaust system as known in the art.  
         [0036]     Another exemplary embodiment of a quantum jet turbine system is illustrated in  FIG. 2 . This embodiment preferably operates using a mixture of air and water as a power generating propulsion source. This is a much more environmentally friendly solution than that of  FIG. 1 . Quantum jet turbine system  1100  includes multiple separate quantum jet engines  1200  housed within a single, common sealed exhaust system, preferably made up of sections A 1 , B 1 , C 1 , D 1  and E 1 . Each quantum jet engine  1200  is housed in section A 1  of the exhaust system, and includes an outer casing  1210  having a sealed, airtight top and converging lower walls  1220  defining upper and lower combustion chambers  1230 A and  1230 B therebetween. Each quantum jet engine  1200  further includes a combustion exit orifice  1240 .  
         [0037]     Within each upper combustion chamber  1230 A are located one or more air nozzles  1250 . Air nozzles  1250  are operably connected to an electric air compressor  2030  through a suitable airtight, sealed feed line (unshown). Flow from the compressor  2030  to air nozzles  1250  may be enhanced by air pump  2020  provided in-line between compressor  2030  and air nozzles  1250 . Also, the air may be fed through chilling mechanisms  2050  prior to reaching air nozzles  250 . Electric air compressors  2030  may receive air/oxygen from a suitable remote source, such as an on-board storage tank or an unshown air intake, which can be in communication with the atmosphere but provided remote from the jet engines  1200 . Suitable filtering may be provided at or between the intake and electric compressors  2030  to prevent large objects from entering the system.  
         [0038]     Also within each combustion chamber  1230 A are located one or more fluid nozzles  1260  for providing water to the combustion chamber. Fluid nozzles  1260  are operably connected to an on-board fluid (water) storage tank  2070  through a suitable airtight, sealed feedline (unshown). Flow from the tank  2070  may be enhanced by a fluid pump  2010  provided in-line between the tank  2070  and fluid nozzles  1260 .  
         [0039]     Because a combustible fuel is not used in this embodiment, there is no spark generator. In its place are provided one or more heating elements  1280  wrapped around inner walls  1210  and  1220  of the combustion chambers and extending downward to preferably cover remaining interior walls of the exhaust system. Insulators may be provided around the exhaust system housing to retain heat inside the exhaust system, keeping the remainder of the craft fuselage unaffected by the heat.  
         [0040]     However, as in the previous embodiment, there is a generator  1400  operably connected through a shaft or other structure to a turbine  1300  having one or more turbine blades placed in the exit path of the combustion exit orifices  1240  as shown. Upon generation of expansion gases exiting the various jet engines  1200  through orifices  1240 , rotation of turbine  1300  will occur, which can be used with known and conventional structure to generate electrical energy from generator  1400 . As in the previous embodiment, electrical output from generator  1400  may be electrically connected to batteries  2040  for recharging purposes and/or may be used to power various auxiliary devices, such as processor  2000 , fluid pump  2010 , air pump  2020 , electric air compressors  2030 , cooling mechanisms  2050  or other devices associated with the engine or craft.  
         [0041]     During operation, quantum jet turbine engines  1200  are started by using either pure distilled water or superchilled air individually or jointly as a propulsion source. Both shown quantum jet engines  1200  will have their upper combustion chambers  1230 A isolated from the lower chambers  1230 B by locking of gas valve locking devices  1290  provided between the upper and lower combustion chambers. At this time, batteries  2040  are activated to raise the temperature of heating elements  1280  to between 200-400° C. or more preferably, in the range of 1000°-3500° C., most preferably between 1000°-2500° C.  
         [0042]     An exemplary heating element  1280  would be an oscillating circuit. This operates by wrapping a coil of wire subjected to a rapidly alternating current around a piece of metal. This induces eddy currents in the metal by induction. The effect is closely related to induced currents discovered by Michael Faraday. The advantage to such a heating element source is that no flame is present and the metal may be treated in a vacuum or in an atmosphere of gas, such as hydrogen. Such heating is not possible with a combustible heat source such as a flame because of either a lack of oxygen or an explosive environment. It would also be possible to provide heating elements  1280  using dielectric heating. With such, when a sheet of non-conducting material is placed between plates of a condenser to which a high frequency oscillator is connected, the rapidly changing electric field in this region causes internal heating of the conductor (such as H 2 O) and the non-conductor (such as chilled air).  
         [0043]     To achieve the higher heat range, preferred heating elements  1280  are of the high heat generator type, which are known and have a capacity to heat a confined vessel from a minimum of 1000° C. up to about 3500° C. The materials of the engines and exhaust are suitably chosen to withstand such heat.  
         [0044]     The compressors and chilling mechanism prepare the air and pressurize the water while the engines are preheated. Once preheated, the high pressure fluid nozzles  1260  will then be opened to spray a fine mist of high pressure water inside both upper combustion chambers  1230 A while the automatic gas locking device  1290  is opened at an appropriate time. At almost the same time, superchilled air is supplied to the combustion chambers. When the system is ready, the initial high pressure steam from within the upper combustion chambers  1230 A will travel at extreme speeds toward the lower combustion chambers  1230 B and further expand and continue its downward path through exit orifices  1240  past turbine  1300 . At this time, processor  2000  can cut off battery current and simultaneously activate the main electric air compressors  2030 , while simultaneously activating the fluid and air pumps and other electrical devices by way of current flowing from generator  1400 , which is suitably sized to power all required electrical devices.  
         [0045]     After passing turbine  1300 , the exhaust gases pass through upper gas expansion area  1510  defined by converging walls  1500  of exhaust section B 1 . In this section, the exiting gases further expand and develop high pressure and temperature ever continuously expanding and rushing toward automatic adjustable gas entry point  1520  where the exiting gases then enter a lower gas reaction area  1620 , formed by diverging walls  1600  of exhaust section C 1 . In lower gas reaction area  1620 , the exiting gases further increase in pressure and temperature and enter the first stage of a multiple stage compound exhaust system  1700  provided at section D 1  of the exhaust system. As shown, there are three stages. Continued flow paths of the exiting gases develop multiple action and reaction forces, acting to further extract kinetic force from the gases and further providing thrust force to propel the jet and associated craft upward. As in the previous example, a suitable exemplary multiple stage compound exhaust system is the 3-stage compound exhaust system disclosed in U.S. Pat. No. 6,367,739, the subject matter of which is hereby incorporated herein by reference in its entirety.  
         [0046]     Upon exiting from compound exhaust system  1700 , exiting combustion gases are received by thrust vector nozzle  1800 , which can be suitably controlled to direct the exiting gases in a desired thrust vector that may be other than in axial alignment with the exhaust system. If additional power generation is needed, additional generators  1900  having turbine blades  1910  may be provided at other positions along the gas flow path, such as after the thrust vector nozzle  1800  as shown in  FIG. 2 .  
         [0047]     As an alternative to water as a primary propulsion source, the inventive quantum jet turbine system can use superchilled air as a primary source of power. In such an application, it will be provided with large, efficient chilling or cooling mechanisms  2050  augmented by efficient air compressors  2030  so as to draw in a large volume of air from the atmosphere, such as through a remotely located intake port.  
         [0048]     In operation, this embodiment will be activated by switching on the heating mechanisms  1280  and the secondary chilling/cooling mechanisms  2050  using battery power from batteries  2040 . When a desired temperature of, for example, 200-400° C. or higher is reached, high pressure superchilled air is pumped into both upper combustion chambers  1230 A by air pumps  2020 , and when a suitable pressure builds up, the automatic adjustable locking devices  1290  will automatically open. This allows the much expanded air to enter the lower combustion chambers  1230 B, where the air further expands while passing by turbine  1300 , which activates main generator  1400 . At this time, processor  2000  can shut off battery supply and run accessories from generator power generated by rotation of the turbine  1300 . Heat inside the system can be maintained by use of insulation installed around the exhaust housing.  
         [0049]     When the system is at work and the required heat is maintained, additional high pressure chilled air can be pumped into the lower gas expansion area  1620  by cold air nozzles  1630  to further increase the speed of the highly accelerated gases, which expand since superchilled air expands when heated. As in the previous embodiment, the expanding gases can pass through the compound multiple stage exhaust system to extract additional kinetic energy from the exiting gases before the gases finally leave the exhaust system. Thus, by providing an extended exhaust system and path length, the efficiency of kinetic energy usage can be increased.  
         [0050]     Although internally provided generators are provided in  FIGS. 1-2 , externally provided generators can also be provided, as illustrated in the alternative embodiments of  FIGS. 3-4 . In particular,  FIG. 3  is otherwise the same as that of  FIG. 1 , but substitutes external turbines  2300  for the internal turbine  300  of  FIG. 1 , and substitutes external generators  2400  for internal generator  400  of  FIG. 1 . Turbines  2300  receive a supply of high speed gas from within upper gas expansion area  510  through valves  2310  and incoming flow lines  2320 . The entering gases rotate the blades within the turbine to generate energy from generators  2400  coupled to respective turbines  2300 . The speeding gases may then be pumped by pump  2340  through exit lines  2360  to the lower gas reaction area  620  through valves  2380 . Similarly,  FIG. 4  is otherwise the same as that of  FIG. 2 , but substitutes external turbines  3300  for the internal turbine  1300  of  FIG. 2 , and substitutes external generators  3400  for internal generator  1400  of  FIG. 2 . Turbines  3300  receive a supply of high speed gas from within upper gas expansion area  1510  through valves  3310  and incoming flow lines  3320 . The entering gases rotate the blades within the turbine to generate energy from generators  3400  coupled to respective turbines  3300 . The speeding gases may then be pumped by pumps  3340  through exit lines  3360  to the lower gas reaction area  1620  through valves  3380 .  
         [0051]     As mentioned previously, the inventive quantum jet turbine propulsion system is well suited to most any type of vehicle. However, it is particularly suited for application to a spacecraft, such as the craft illustrated in  FIG. 5 . This craft  3000  includes various quantum jet turbine propulsion systems  100  spaced around the craft, and may further include other propulsion systems, such as high frequency oscillators  4000  shown below cabin  5000  having windows  5050 . Additional details of such an exemplary craft can be found in Applicant&#39;s incorporated co-pending U.S. patent application Ser. No. ______ (Attorney Docket No. 104148).  
         [0052]     As mentioned earlier, the quantum jet turbine engine system preferably has two or more smaller jet engines within a single, common exhaust. This has been found to have improved kinetic energy by using the same amount of fuel, which travels at higher velocities within the smaller jet engines. For example, knowing that kinetic energy KE=  1 / 2 MV 2 , where M is mass and V is velocity, it can be shown how multiple jet engines can achieved increases in both efficiency and output.  
         [0053]     In a mono jet configuration, assuming a 100 lb. mass of high speed gases in the combustion chamber and a gas velocity of 32 feet/second, KE=½MV 2 =100/2×32 2 =51,200 foot pounds of work. In a dual jet configuration, the 100 lb. mass can be equally distributed between the two smaller jets, which operate at a higher gas velocity of 64 feet/second. KE=1/2MV 2 =50/2×64 2 =102,400 foot pounds of work for each engine, for a total of 204,800 foot pounds. Similarly, in a tri engine configuration, which could operate at a higher gas velocity of 128 feet/second, KE=1/2MV 2 =33.3/2×128 2 =272,794 foot pounds of work for each engine, for a total of 818,382 foot pounds. For a quad jet configuration, which would operate at yet a higher velocity because of its smaller jet sizes, KE=½MV 2 =25/2×256 2 =819,200 foot pounds of work for each engine, for a total of 3,276,800 foot pounds.  
         [0054]     When water is used as a propulsion source, steam serves as the exhaust gas. If the exiting and expanding high pressure steam (H 2 O) is cooled in the exhaust chamber while keeping pressure high, the steam can be reverted back to a liquid form, where it can be pumped out and returned to the fuel tank for reuse.  
         [0055]     While specific aspects of the invention have been described with respect to preferred embodiments of the invention, these are not intended to be limiting. Various modifications can be made without departing from the scope of the appended claims.

Technology Classification (CPC): 5