Abstract:
A turbine is operatively connected to load structure, to transmit rotary drive thereto, with two-phase flow nozzle receiving pressurized flow to rotate the turbine, the nozzle structure configured to expand flow consisting of two or more of the following phases:
       i) gas   ii) liquid   iii) gas and liquid mixture   iv) supercritical gas and liquid mixture, and with efficient conversion of enthalpy.

Description:
BACKGROUND OF THE INVENTION 
     This invention relates generally to fluid driven turbines and more generally to those having a variable phase fluid driving the turbine. The variable phase may be a mixture of a gas and liquid phase; or a supercritical phase; or a supercritical phase that transitions within the device to a mixture of gas and liquid or to a pure gaseous phase; or a liquid phase that transitions within the device to a mixture of gas and liquid; or a liquid phase that transitions within the device to a mixture of gas and liquid and then subsequently transitions also within the device to a pure gaseous phase. Apparatus that efficiently converts all these fluid combinations is necessary for turbines and heat engines that optimize the production of power from heat energy, and from pressure energy in industrial processes. 
     Turbines are widely used in industry to convert energy in liquid streams or gas streams to shaft power. Less common, but also used are turbines to convert energy in two-phase (gas and liquid) streams to shaft power. A further requirement can be the conversion of supercritical streams and/or streams that transition from a single phase to two-phase streams. Still further applications exist for the conversion of energy in two-phase streams that transition to a gaseous stream. 
     At present, the turbines for each type of stream are unique to that stream. That is, a turbine configured to be gas driven is not readily usable for liquid or two-phase flow. For example, attempts to use radial inflow gas turbines for two-phase flow have resulted in poor performance and damage because the directions of centrifugal body forces are such as to throw liquid backwards into the nozzle blades. 
     Applicants herein believe that no efficient turbine design exists for the case of a two-phase stream which transitions to a gaseous stream within the turbine, or for a supercritical stream which transitions to a two-phase stream within the turbine or for a supercritical stream which transitions to a two-phase stream that subsequently transitions to a gaseous stream within the turbine. These instances will be referred to herein as “Transition Flows”. 
     Certain applications for turbines require the use of different types of fluid streams for differing conditions, as well as the use of Transition Flows. For example, a low temperature geothermal power system may require use of a gas stream or a two-phase flow stream, depending upon the temperature and working fluid used in the power producing cycle. To maximize power production, the geothermal power system may require a turbine to start in the supercritical flow regime and handle the transition to a two-phase stream within the turbine. 
     At present, to provide an efficient power conversion system, a new or specialized turbine must be designed, manufactured and qualified for each application. This is costly and time consuming and reduces flexibility, if the thermal characteristics of a given application change with time. There is need for an efficient turbine that can be driven by gas, or liquid or two-phase fluid flow. There is also a need for an efficient turbine that can be driven by Transition Flows. 
     SUMMARY OF THE INVENTION 
     It is a major object of the invention to provide a solution or solutions to the above described problems and needs. 
     An object of the present invention is to provide an improved turbine characterized by one or more of the following:
         a) use for two-phase flow to generate power efficiently;   b) use for Transition Flow to generate power efficiently;   c) use for either gas, liquid, two-phase or Transition Flow, with minor adjustments to a component part, or parts, such adjustments typically concerning nozzle inserts and blade adjustments.       

     A further object is to provide a turbine that can operate efficiently with changes in input two-phase flow stream or Transition Flow stream parameters, such as inlet pressure or flow rate. 
     Yet another object is to provide a turbine that will separate liquid from the gas stream leaving the turbine to maximize the effectiveness of any downstream heat rejection or separation equipment. 
     An added object is provision of a turbine and electric generator assembly that can be used for either gas, liquid, two-phase flow or Transition Flow, and that requires no external seals, referred to herein as the Variable Phase Turbine Generator Assembly (VPTGA). 
     Another object is provision of a turbine, electric generator and pump assembly that can be used for either gas, liquid or two-phase flow with no external seals, referred to herein as the Variable Phase Turbine Generator Pump Assembly (VPTGPA). 
     Another object is provision of a compressor means connected to the shaft of the VPT to utilize the shaft power to add compression energy to a separate gas stream from a process, or to the separated gaseous stream from the exit of the VPT. 
     Another object of the invention is provision of a pump means connected to the shaft of the VPT to use the power created by the VPT to pump another stream. 
     An additional object in provision of variable phase turbine apparatus that comprises: 
     a) nozzle means operable to discharge a fluid medium of liquid, supercritical fluid or a mixture of liquid and gas with conversion of medium enthalpy to kinetic energy in a directed stream of a mixture of gas and liquid, supercritical fluid or pure gas, said directed stream characterized by the chemical composition of the fluid medium and the thermodynamic conditions of the enthalpy conversion process, said nozzle means directing the flow at blade means, for displacing said blade means, 
     b) the blade means configured to maximize the conversion of the kinetic energy of said directed stream into torque acting upon rotor means carrying said blades, 
     c) said rotor means to which said blades are attached transmitting the torque to a shaft to which the rotor and a load are attached, 
     d) casing means configured to confine and direct the medium and which contains bearings and seals to enable the shaft to transmit the torque, and 
     e) shroud means configured to prevent liquid which has transferred kinetic energy to the blades from contacting the casing and from being re-directed to contact the moving blades, causing losses in torque. 
     A further object is to provide for adjusting turbine nozzle flow through configuration as a function of input pressurized fluid phase composition, to maximize kinetic energy, minimize particle sizes, or optimize the combination of kinetic energy and particle size of nozzle discharge to turbine blades. 
     As will be seen, means may be provided at one end of the turbine and responsive to positioning of nozzle pintle means to vary the flow area of the nozzle means by axial translation of said pintle means, to maximize kinetic energy minimize particle sizes, or optimize the combination of kinetic energy and particle size leaving the nozzle means, for two or more flow phases. 
     These and other objects and advantages of the invention, as well as the details of an illustrative embodiment, will be more fully understood from the following specification and the drawings. 
    
    
     
       DRAWING DESCRIPTION 
         FIG. 1  is a section taken through a variable phase nozzle; 
         FIG. 2  is a block diagram as respects nozzle option; 
         FIG. 3  is a comparison of two nozzle pressure profiles and the resulting bulk velocities and particle sizes; 
         FIG. 4  is a section taken through preferred variable phase turbine apparatus incorporating a hermetically enclosed electrical generator and with variable nozzles; and  FIGS. 4   a ,  4   b  and  4   c  are enlargements; 
         FIG. 5  is a section taken through turbine apparatus, showing another application; 
         FIG. 6  is a section through a variable phase turbine compressor; 
         FIGS. 7 and 8  are views that show dual nozzle rows, as may be employed in the  FIG. 4  apparatus; 
         FIG. 9  is a section showing full admission nozzle; and 
         FIG. 10  is a perspective view showing vanes of full admission nozzles. 
     
    
    
     DETAILED DESCRIPTION 
     A representative variable phase nozzle  100  is shown in  FIG. 1 . A liquid enters the nozzle with low velocity and high pressure at  1 . The pressure is reduced in a converging section  101  resulting in the flashing of the liquid to vapor. The vapor formation can occur as a central pocket,  6 . 
     Efficient acceleration of the liquid phase by a gas phase in the nozzle requires the mixing of the liquid phase with the gas phase. Should the liquid be predominately on the nozzle wall and the gas remain as a central pocket, the coupling of the gas shear forces with the liquid is inefficient. To promote removal of the liquid from the wall a plate,  7 , is shown as provided to remove the liquid from the wall and mix the liquid with the gas. Plate  7  has an opening defined by radially inwardly concave wall  7   a.    
     Further acceleration of the liquid is achieved by lowering the pressure in a converging section. The shear forces of the accelerating gas result in a breakup of the initially large diameter droplets,  8 , to smaller diameter droplets at  9 . The smaller diameters result in greater surface area and an improved coupling of the gas with the liquid. Depending upon the pressure ratio, the velocity of the mixture can reach sonic velocity as at a reduced area throat,  3 . In this case the nozzle area is increased as at  4 , resulting in the flow leaving the nozzle at  5 , being supersonic. Typically, the angular displacement of each blade leading edge from the perpendicular to the axis of the nozzle means of between 1 degree to 15 degrees counter to the rotational direction. Also, for a directed stream of a mixture of liquid and gas, the blading means has an initial section with a gradual angle optimized to minimize the sum of momentum losses and friction losses when the stream impacts the blade surface. Also, for the case of a directed stream of a mixture of liquid and gas, the blading means is configured to increase the hydraulic diameter of liquid flowing on the surface, thereby reducing friction losses. Also, for the case of a directed stream of a mixture of gas and liquid, the blade means is configured to produce a trajectory of liquid leaving the surface of the blades thereby to impart a tangential component of the velocity relative to the shaft centerline, causing the liquid to be separated from the gas phase and to enter a passage provided in the casing to capture the liquid. Alternatively, the method of operation includes adjusting nozzle flow through configuration as a function, or coded function of input fluid phase composition, to optimize kinetic energy and particle size in nozzle discharge incident on turbine blades. 
     A design code or program may be used to control an actuator  160  to axially control a pintle  10  (see  FIG. 4   a ) to minimize the droplet size and to maximize nozzle efficiency. Minimization of the droplet size is important to increase the surface area, to promote heat and mass transfer within the nozzle and to produce a homogeneous fluid that will maximize the efficiency of turbine blading upon which the fluid acts. The code can analyze and design the flow in nozzles for single phase, two-phase, supercritical flow or any combination. See  FIG. 2  functional block diagram. The code enables the determination of the optimum pressure profile to maximize the efficiency of expansion. See sensor  161  to sample droplet size, with feedback signaling at  162  to the programmed controller  163 . 
     For a two-phase nozzle, a major loss is the slip. Slip is defined as the velocity difference between the gas phase and the liquid phase:
 
 S=V   g   −V   l  
 
     where
         S=slip   V g =gas velocity   V l =liquid velocity
 
Slip occurs as a result of the pressure gradient and droplet size. However, the droplet size, in turn, is determined by the slip and surface tension:
 
 D= 12 σ/ρ   g   S   2  
       

     where
         σ=surface tension   ρ g =density of gas
 
Smaller droplets result in higher surface area per unit mass, which results in lower slip and less loss. However, high values of slip are needed to produce small droplets. The usual design approach is to use a gradual pressure gradient to minimize the difference between the gas velocity and the liquid velocity at any point. However, this design approach can result in a value of the averaged velocity which is lower than the optimum value.
       

     An additional consideration is that making many small droplets requires more energy, than making fewer large droplets. Thus, there is a trade-off between optimizing particle size, and therefore slip, and optimizing kinetic energy at the nozzle exit. It is, therefore, crucial to predict and configure the nozzle to optimize the flow going to the turbine rotor. The nozzle code methodology, as in  FIG. 2 , is implemented to achieve this. 
     In order to minimize particle size and optimize averaged velocity at the exit of the nozzle the pressure gradient, and hence slip, is preferably maximized at the inlet regions of the nozzle. This unexpected result is a consequence of using the large slip to create the smallest possible droplet size, in a region where the overall kinetic energy is small. A nozzle, representative of this phenomenon, is illustrated in  FIG. 1 . The loss, while locally large in comparison with the local kinetic energy, is small compared to the final kinetic energy of the nozzle. Thus slip and losses are minimized in the regions of the nozzle having high kinetic energy. 
       FIG. 2  illustrates the method used, the pressure profile being varied as an independent input parameter to the nozzle code until the optimum design is determined. 
       FIG. 3  illustrates an application of the design method to the two-phase nozzle of  FIG. 1 . As shown, the droplet size is increased from 3 microns to 4 microns. The resulting slip is correspondingly increased in the high velocity downstream regions of the nozzle resulting in an increase in the averaged exit velocity,  10   a , from 719 feet per second for the nozzle configuration of  FIG. 1  to 730 ft/s for the optimized nozzle. This surprising result stems from reduced friction losses as well as reduced droplet breakup energy required. Because the difference in droplet size is small, the increased velocity is more important. Variations in flow to the nozzle can be controlled with a throttling valve. However, reducing the flow using a valve causes a loss in efficiency. To enable efficient operation at part flow, an adjustable center body with a special contour, “the pintle”, is used, and shaped with taper, as shown. 
       FIG. 4   a  shows the use and operation of such a pintle  10 , having a smoothly decreasing cross sectional area in the axial direction toward its pointed tip. As the pintle is translated in the direction of the throat,  16 , a gradual decrease in flow area from the nozzle inlet,  18 , to the throat  18   a  results. This action enables lower flow rates to efficiently accelerate to the same velocity at the throat at the design flow rate with the full throat area available. The pintle has a radially outwardly facing concave side wall that faces toward receptacle wall  18   b  that tapers toward throat  16 . 
     As also seen in  FIG. 4   a , pintle is attached to a sliding rod,  13 , which in turn is attached to actuator piston,  14 , which has a sliding seal with the housing,  19 . In the variation shown, a spring,  12 , is compressed by the action of a high pressure fluid,  15 , admitted to the face of the piston. The force from the piston causes the pintle to have a closing or area reduction action. In this version, the throat area is normally open. The piston and high pressure fluid can be provided on the reverse side of the spring to produce a normally closed throat area. The arrangement depends upon process requirements. 
     Expansion of the flow to the proper pressure in the throat results in an efficient acceleration of the flow to that point. Expansion of the flow from the throat to the nozzle causes some over-expansion losses, which have been found to be minimized when two fluid phases are present. Expansion in the nozzle of a mixture of a gas and liquid phase; or of a supercritical phase; or of a pure gaseous phase; or of a liquid phase that transitions to a mixture of gas and liquid; or a liquid phase that transitions to a mixture of gas and liquid and then subsequently transitions to a pure gaseous phase produces a well collimated nozzle exit stream at  19 ′, of liquid and gas or dry gas having kinetic energy. 
     The nozzle exit stream is subsequently directed onto rotating blades,  20 , attached to a blade carrying rotor,  21 , which is in turn attached to axially extending tubular shaft,  22 , supported by bearings,  25 . The kinetic energy of the nozzle exit stream is transferred to the blades producing a torque on the rotor and shaft. The design of the blade profile depends upon whether the nozzle exit stream is a liquid and gas mixture, or a dry gas. If the nozzle exit stream is a liquid and gas mixture, the design of the blade profile further depends upon the droplet size. 
     The flow  23  leaving the blades passes to the outlet,  24 . If the flow leaving the blades is a liquid and gas mixture, sufficient kinetic energy can be left to produce swirl causing separation of the liquid from the gas with an internal separator. 
     The variable phase turbine generator apparatus version shown in  FIG. 4  is configured for use with an electrically non-conducting fluid, such as liquefied natural gas or liquid ethylene or a refrigerant. The shaft is attached to a generator rotor,  26 , the rotation of which causes generation of electric power in a stator,  27 . See  FIG. 4   b  and  4 . Power is removed by a conductor  27   a  and transmitted at  41   a  through the casing,  41 , using an insulating feedthrough means  29 . Nozzle  180  extends at one end of the generator, and terminates at exit  19 ′ offset from the rotor axis  35   a , adjacent the circular path of rotation of the blades. Annular body  105  supports the casing  41  as well as the angularly directed nozzle. 
     The fluid is supplied to the VPT through an inlet port,  30 . The fluid is directed through an annulus,  44 , to the nozzle inlets,  18 , exposed to  44 . A highly compact and efficient design is thereby achieved. 
     A portion of the fluid flow is diverted through a port,  31 , in an inner casing,  40  near entrance  30   a  to outer casing  41 . Casing  40  supports the generator casing  41  and bearings. A portion of the diverted fluid flows to the bearing cavities,  33 , and subsequently through the bearings, to provide lubrication and heat removal. The fluid leaving the bearings is discharged through orifices,  34 , which communicate with passage,  35 , within the shaft. That passage endwise communicates with the pressure of the fluid leaving the turbine,  23 , which is lower than the pressure of the fluid entering the nozzles  18 , and that diverted,  31 . The passage  35  within the shaft communicates with the upper end of the shaft,  39 , opposite the turbine rotor, resulting in a low pressure at the shaft end. Nozzles  18  are spaced annularly about the shaft axis  35   a.    
     Another portion of the diverted fluid flows through the gap  32  between the generator rotor and the stator, removing heat generated by electrical and frictional losses. This portion of the fluid flows through the bottom bearing, providing lubrication and heat removal before flowing at  34  into the low pressure passage  35  within the shaft. 
     The weight of the shaft and rotor and the frictional forces due to the fluid flowing downwardly in the gap would produce a downward or axial force on the bearings.  FIG. 5  shows the method of force alleviation, with another portion of the diverted fluid flowing through the gap,  47 , formed by a throttling disc  36  attached to the shaft and a stationary member,  45 , attached to the inner casing. The downward force has a tendency to move the shaft in the downward direction opening the gap  47 , causing the loss of throttling and a high pressure in the cavity,  37 , below the face of another disc,  38 , attached to the shaft. The high pressure and force on the upper disc causes the shaft to move upward and the gap to close, resulting in a throttling action, reducing the pressure and force on the face of the upper disc until the upward force just balances the downward force. At this point there is no net axial force on the bearings and the balance is automatically maintained. 
     Shroud  110  below blades  20  and body  105  prevents discharged liquid from contacting casing  41  and from redirection to contact the moving blades causing losses in torque. 
     Another application is to use the variable phase turbine to drive a compressor.  FIG. 5  shows a single stage centrifugal chiller driven by the shaft,  61 , from the VPT, which has no external seals. Flow,  56 , enters the compressor and is increased in pressure by the moving vanes,  47 . A further increase in pressure occurs in the diffuser,  57 . The flow is then collected in the volute,  58 , and leaves through a port  59 . The fluid compressed can be the same as, or different from, the fluid operating the Variable Phase Turbine. 
     A portion of the fluid operating the variable phase turbine, is admitted through a pipe,  48 , to a cavity,  49 . The fluid flows through the bearings,  50 , to lubricate them, and into passages,  51 , in the shaft,  61 . The fluid then flows through a central passage,  53 , in the shaft and mixes with the flow,  54 , leaving the moving blades. The mixed flow,  55 , leaves the structure through a port. The VPT nozzle structure,  200 , and blading  201 , is generally the same as in  FIGS. 1-4 . 
     Seals,  52 , are provided to prevent the fluid operating the variable Phase Turbine, from mixing with the compressor fluid. 
     A combined variable phase turbine and multistage compressor is shown in  FIG. 6 . The VPT bladed rotor,  62 , transfers torque to a shaft,  63 , causing compressor rotors,  64 , attached to the shaft to rotate. The shaft is supported on bearings,  65 . 
     The vapor to be compressed enters the compressor casing,  76 , through a port,  77 . The vapor is compressed by the first rotor  64  and discharged into a stationary diffuser,  79 , where the pressure of the vapor is increased further. The vapor then flows into a cross-over channel,  80 , and is ducted inwardly at  81 , to the inlet of the next rotor  64 . The process continues to the last rotor where, after the vapor is discharged into the last diffuser and the pressure increased, the vapor leaves the casing through a port,  78 , and flows to the process. 
     A portion,  69 , of the liquid,  82 , driving the VPT is diverted to chambers,  83 , in proximity to the bearings. The liquid flows through the bearings to provide lubrication and cooling. Seals,  68 , are provided to isolate the liquid from the vapor being compressed. The liquid used for bearing lubrication discharges through a passage or passages  70 , into a passage,  71 , in the shaft and subsequently is endwise discharged at  72 , into the exhaust region of the VPT rotor, and mixes with the flow leaving the blades,  73 . 
     The pressure difference across the compressor rotors typically produces an axial force on the bearings. To counteract this force, another portion,  83 , of the diverted fluid flows through the gap,  74 , formed by a throttling disc,  84 , attached to the shaft and a stationary member,  85 , attached to the casing. The axial force from the pressure difference has a tendency to move the shaft, opening the gap, causing loss of throttling and a high pressure in the cavity  86 , below the face of another disc,  87 , attached to the shaft. The high pressure and force on the upper disc causes the shaft to move opposite to the pressure difference and the gap to close, resulting in a throttling action, reducing the pressure and force on the face of the second disc until the force on the disc just balances the pressure force. At this point there is no net axial force on the bearings and the balance is automatically maintained. 
     The liquid flowing through the disc enters a chamber  75 , and is discharged through the central passage,  71 , in the shaft to the exit of the VPT rotor. 
     For a given rotor speed and nozzle exit velocity there is a limit to the flowrate that can be provided to the turbine by a single row of axisymmetric nozzles. That limit is: 
     
       
         
           
             
               maximum 
               ⁢ 
               
                   
               
               ⁢ 
               flow 
               ⁢ 
               
                   
               
               ⁢ 
               rate 
             
             = 
             
               
                 
                   
                     
                       π 
                       ⁡ 
                       
                         ( 
                         
                           ρ 
                           ⁢ 
                           
                               
                           
                           ⁢ 
                           V 
                         
                         ) 
                       
                     
                     b 
                   
                   ⁢ 
                   
                     
                       
                         NV 
                         2 
                       
                       ⁡ 
                       
                         ( 
                         
                           U 
                           C 
                         
                         ) 
                       
                     
                     2 
                   
                 
                 
                   4 
                   ⁢ 
                   
                     ω 
                     2 
                   
                 
               
               ⁢ 
               
                 
                   sin 
                   2 
                 
                 ⁡ 
                 
                   ( 
                   
                     2 
                     ⁢ 
                     α 
                   
                   ) 
                 
               
               ⁢ 
               
                 
                   tan 
                   2 
                 
                 ⁡ 
                 
                   ( 
                   
                     π 
                     N 
                   
                   ) 
                 
               
             
           
         
       
     
     where
         (V) b =bulk averaged mass flux   N=number of nozzles   V=Velocity leaving nozzles   (U/C)=Tip/Jet velocity ratio   ω=angular frequency   α=nozzle angle       

     To provide more flowrate at the optimum subtended angles while keeping the rotor speed constant, a second row of axisymmetric nozzles, radially inboard of the first row can be used.  FIG. 7  shows the arrangement of an outer row of nozzles,  86 , and an inner row,  87 , while maintaining the angle between the nozzle centerline and the plane normal to the centerline of the rotor. 
       FIG. 8  shows that the areas  88 , normal to the plane perpendicular to the centerline of the turbine rotor, and the subtended angle  89 , from axis  89   a  are closely similar for the nozzle first row and second row. The similarity enables efficient conversion of the kinetic energy from both rows of nozzles by the blades of the VPT. Each area  88  corresponds to a cross section, at a nozzle. 
     Another method to provide more flow at the optimum subtended angles is to provide a nozzle formed by two contoured surfaces with dividing vanes inserted between the surfaces to guide the expanding flow at the proper angle.  FIG. 9  shows cross sections  90  and  91 , of the two contoured annuli  92  and  93  that incorporate such surfaces guiding vanes  101  extend between such surfaces  92   a  and  93   a . Generally high pressure flow is provided from a plenum,  94 , formed by assembly of mating parts, and enters the nozzle passage,  95 , at a generally inclined angle to the plane of the passage, typically 15-20 degrees. The flow expands to the exit,  96 , where it leaves the nozzle at the same inclination and impinges on turbine blades,  97 .  FIG. 10  shows the annuli  92  and  93  having the nozzle surfaces. One of the surfaces,  100 , is shown for the lower  93 . The guiding vanes,  101 , are shown to make an angle,  102 , with the plane perpendicular to the axis of the nozzle structure. This angle is typically between 15-20 degrees. 
     In the above, the medium is one of the following:
         x 1 ) 1,1,12-Tetrafluoroethane, i.e., R134a   x 2 ) ii Difluoro-1,1-ethane, i.e., R152a   x 3 ) 1,1,1,2,3,3,3-heptafluoropropane, i.e., R227ea   x 4 ) 1,1,1,2,3,3-hexafluoropropane, i.e., R236ea   x 5 ) 1,1,1,3,3-pentafluoropropane, i.e., R245fa   x 6 ) 1,1,2,2,3-pentafluoropropane, i.e., R245ca   x 7 ) 1,1-dichloro-2,2,2-trifluoroethane, i.e., R123   x 8 ) CO2   x 9 ) CH4   x 10 ) propane   x 11 ) ethylene   x 12 ) propelene   x 13 ) water   x 14 ) nitrogen   x 15 ) mixtures where the above fluids comprise 50% or more of the mixture,       

     Also disclosed herein are the contents of all claims.