WO2010096540A2 - Système de production d'électricité thermodynamique - Google Patents

Système de production d'électricité thermodynamique Download PDF

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Publication number
WO2010096540A2
WO2010096540A2 PCT/US2010/024563 US2010024563W WO2010096540A2 WO 2010096540 A2 WO2010096540 A2 WO 2010096540A2 US 2010024563 W US2010024563 W US 2010024563W WO 2010096540 A2 WO2010096540 A2 WO 2010096540A2
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WO
WIPO (PCT)
Prior art keywords
heat
loop
blade
working fluid
thermodynamic
Prior art date
Application number
PCT/US2010/024563
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English (en)
Other versions
WO2010096540A3 (fr
Inventor
Robert F. Waterstripe
Gary P. Hoffman
Richard L. Willoughby
Original Assignee
Thermal Power Technology Llc
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Thermal Power Technology Llc filed Critical Thermal Power Technology Llc
Priority to EP10705506A priority Critical patent/EP2399003A2/fr
Priority to CN2010800081066A priority patent/CN102405332A/zh
Publication of WO2010096540A2 publication Critical patent/WO2010096540A2/fr
Publication of WO2010096540A3 publication Critical patent/WO2010096540A3/fr

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01K—STEAM ENGINE PLANTS; STEAM ACCUMULATORS; ENGINE PLANTS NOT OTHERWISE PROVIDED FOR; ENGINES USING SPECIAL WORKING FLUIDS OR CYCLES
    • F01K3/00—Plants characterised by the use of steam or heat accumulators, or intermediate steam heaters, therein
    • F01K3/02—Use of accumulators and specific engine types; Control thereof
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
    • F01D1/02—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines
    • F01D1/026—Impact turbines with buckets, i.e. impulse turbines, e.g. Pelton turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01K—STEAM ENGINE PLANTS; STEAM ACCUMULATORS; ENGINE PLANTS NOT OTHERWISE PROVIDED FOR; ENGINES USING SPECIAL WORKING FLUIDS OR CYCLES
    • F01K25/00—Plants or engines characterised by use of special working fluids, not otherwise provided for; Plants operating in closed cycles and not otherwise provided for
    • F01K25/08—Plants or engines characterised by use of special working fluids, not otherwise provided for; Plants operating in closed cycles and not otherwise provided for using special vapours
    • F01K25/10—Plants or engines characterised by use of special working fluids, not otherwise provided for; Plants operating in closed cycles and not otherwise provided for using special vapours the vapours being cold, e.g. ammonia, carbon dioxide, ether

Definitions

  • the present invention relates to externally heated engines. More particularly the invention relates to improvements in efficiency and performance of externally heated engines operating at low temperatures and pressures.
  • Turbine style engines that employ liquid fluid flows are the most limited. Unless one has access to a dam, with a large head of water behind it, or a particularly rapidly flowing stream with a large drop in elevation, one cannot produce significant amounts of power. Without a dam or a stream it is simply not feasible or efficient to heat the liquid sufficiently, or to pump it uphill far enough and cheaply enough, to obtain a useful net output. Similarly, a paddle wheel type structure such as found on certain steam ships for instance, require a separate source of motive power, such as a steam engine, to operate them.
  • Turbine type engines that employ flows of a gaseous fluid hold more promise. It is practical to employ fluids in the gas phase to power engines, as in steam locomotives for example. Other types of hot gas turbines are also well known in the prior art, and can operate effectively. In virtually all of these cases however, the required temperatures and pressures to which the gas must be raised are very high. It is not uncommon for such engines to reach temperatures of hundreds of degrees Fahrenheit, and at the same time to operate at pressures of hundreds of PSI. In general, this means that a source of combustion must be specifically provided and operated in conjunction with the engine, for the sole benefit of the engine, in order to reach the operating levels required.
  • Old style steam locomotives and stationary steam engines for instance ran on large coal fires, operating in conjunction with pressure-raising pumps, to produce the required levels.
  • Such engines were well known for exploding at inopportune times.
  • Gas turbine engines such as those used at electrical generation stations, also employ very high temperatures and pressures.
  • Jet turbine engines such as those employed on aircraft, also produce extremely high temperatures in their combustion chambers, and they further employ multiple stages of compression to reach the desired pressures and temperatures.
  • the present invention is directed to a heat engine and power generating system that avoids high temperatures and pressure and relies instead on relatively low temperature heat sources and low pressure operating fluids to generate energy.
  • the system will function without the need for our own dedicated source of combustion in order to operate and will operate at a relatively high efficiency, and produce significant amounts of power.
  • the engine is designed to operate on low temperature waste heat left over from other processes, or to operate on low temperature solar or geothermal power, for instance.
  • U.S. Patent No. 3,501,249 to Scalzo is directed to turbine rotors and particularly to structure for locking the turbine rotor blades in the periphery of the blade supporting disk.
  • U.S. Patent No. 4,073,069 to Basmajian discloses an apparatus comprising a turbine rotor wheel made of a central circular disc with arc-bent plate turbine blades mounted on and bonded to the disc at close and regular intervals around the disc periphery and a stator- housing with a transparent cover for enclosing the turbine wheel, holding one or more feed nozzles and providing a stator reaction mount for the nozzles, the wheel and its housing being mounted from an instrument chassis containing parameter adjusting means and turbine output adjusting and measuring means to provide a compact, economical demonstrator of turbine operation.
  • U.S. Patent No. 4,400,137 to Miller et al discloses a rotor assembly and methods for securing rotor blades within and removing rotor blades from rotor assemblies.
  • the rotor assembly comprises a rotor disc defining a plurality of blade grooves, and including a plurality of tenons disposed between the blade grooves and defining a plurality of pin sockets radially extending inward from outside surfaces of the tenons; and a plurality of rotor blades, each blade including a root disposed within a blade groove to secure the blade against radial movement, and a blade platform overlaying a tenon and defining a radially extending pin aperture.
  • the rotor assembly further comprises a plurality of locking pins radially extending through the pin apertures and into the pin sockets to secure the rotor blades against axial movement, each pin including a head and a base to limit radial movement of the pin.
  • U.S. Patent No. 4,421,454 to Wosika discloses a full admission radial impulse turbine and turbines with full admission radial impulse stages.
  • the turbines are of the single shaft, dual pressure type. Provision is made for utilizing working fluid exhausted from the high pressure section, in which the radial impulse stage(s) are located, in the low pressure section which contains axial flow turbine stages.
  • the (or each) radial impulse stage in the dual pressure turbine has a rotor or wheel with buckets or pockets oriented transversely to the direction of wheel rotation and opening onto the periphery of the wheel.
  • Working fluid is supplied to the buckets via nozzles formed in, or supported from, a nozzle ring surrounding the turbine wheel and aligned with the entrance ends of the buckets.
  • U.S. Patent No. 4,502,838 to Miller et al discloses buckets of a turbine wheel that are formed as a series of equally spaced, overlapping U-shaped passages in the rim of a wheel blank. In the machining operation, an island is left as the inner segment of the curved portion of the U and this is used in combination with labyrinth seals to provide a fluid seal between the inlet and the outlet portion of each bucket.
  • U.S. Patent No. 5,074,754 to Violette discloses a retention system for a rotor blade that utilizes the combination of a fixed retention flange and a removable retention plate with a closed-sided retention member. This system enables the rapid replacement or removal of the rotor blade for inspection, maintenance, or replacement purposes without requiring removal of surrounding major engine components or structural members.
  • the rotor blade is installed in a retention member contained in a rotatable hub (not shown) by inserting an outwardly extending portion of a shaped blade root of the rotor blade below a radially- inwardly projecting shaped flange peripherally disposed within the interior of the retention member's structure.
  • a removable shaped retention plate which is releasably secured to, and adapted to mate with, the retention member, then captures and secures another outwardly extending portion of the shaped root of the rotor blade with a releasable fastener.
  • the shaped root is secured within the retention member without a direct bolted connection. Preloading the fastener induces compressive loading among the system components, resulting in the attenuation or elimination of fretting and wear of their respective component surfaces.
  • the prior art includes many examples of power systems that attempt to capture waste heat from a primary heat source and reuse the energy in a secondary power system.
  • U.S. Patent No. 3,822,554 to Kelly discloses a heat engine operating between temperatures Tl (low) and T2 (high) includes separate vapor closed-cycle motor and pump systems, in heat-exchange relation at Tl and T2, and heat-exchangers between the condensates of said systems.
  • U.S. Patent No. 3,953,973 to Cheng et al discloses a heat engine, or a heat pump, in which the working medium is subjected alternatively to solidification and melting operations.
  • a working medium is referred to as an S/L type working medium that is subjected to cyclic operations, each cycle comprises of a high temperature melting step conducted under a first pressure, and a low temperature solidification step conducted under a second pressure.
  • Each heat pump cycle includes a high temperature solidification step conducted under a first pressure and a low temperature melting step conducted under a second pressure.
  • the first pressure and the second pressure are a relatively high pressure and a relatively low pressure, respectively.
  • an aqueous medium is used the two pressures are a relatively low pressure and a relatively high pressure, respectively.
  • the operation of a heat pump is the reverse operation of a heat engine.
  • U.S. Patent No. 4,292,809 to Bjorklund discloses a procedure for converting low- grade thermal energy into mechanical energy in a turbine for further utilization.
  • the procedure is characterized in that a low-grade heating medium and a first cooling medium are evaporated in a heat exchanger.
  • the steam is carried to a turbine for energy conversion and moist steam is carried from here to a heat exchanger for condensing.
  • the condensate is pumped back to the heat exchanger.
  • the heat exchanger is common to the steam turbine circuit and a heat pump circuit in such a manner that the heat exchanger comprises a condenser for the steam turbine circuit and an evaporator in the heat pump circuit.
  • the heat removed in connection with condensing can be absorbed by a second evaporating cooling medium the steam of which is pumped via a heat pump to a heat exchanger which is cooled by cooled medium from the heat exchanger and where condensing takes place.
  • the condensate is carried via an expansion valve back to the heat exchanger while outgoing cooled medium from the heat exchanger is either heated in its entirety to a lower level than the original temperature at the commencement of the process or else a partial flow is reheated to a level that is equal to or higher than the original temperature at the commencement of the process and returned to the heat exchanger.
  • the hot gas of the heat pump is used for extra superheating of the ingoing first evaporated cooling medium supplied to the turbine.
  • U.S. Patent No. 4,475,343 to Dibelius et al discloses a method for the generation of heat using a heat pump in which a heat carrier fluid is heated by a heat exchanger and compressed with temperature increase in a subsequent compressor, heat is delivered therefrom to a heat-admitting process; the fluid is then expanded in a gas turbine, producing work, and afterwards its residual heat is delivered to a thermal power process, the maximum temperature of the energy sources of which, that provide work for the compressor, lies below the temperature of heat delivery.
  • the main heat source can consist of an exothermic chemical or nuclear reaction and the heat-admitting process can be a coal gasification process.
  • the work in the compressor is furnished essentially by the gas turbine and the thermal power process.
  • U.S. Patent No. 4,503,682 to Rosenblatt discloses an engine system that includes a synthetic low temperature sink which is developed in conjunction with an absorbtion- refrigeration subsystem having inputs from an external low-grade heat energy supply and from an external source of cooling fluid.
  • a low temperature engine is included which has a high temperature end that is in heat exchange communication with the external heat energy source and a low temperature end in heat exchange communication with the synthetic sink provided by the absorbtion-refrigeration subsystem. It is possible to vary the sink temperature as desired, including temperatures that are lower than ambient temperatures such as that of the external cooling source. This feature enables the use of an external heat input source that is of a very low grade because an advantageously low heat sink temperature can be selected.
  • 5,421,157 to Rosenblatt discloses a low temperature engine system that has an elevated temperature recuperator in the form of a heat exchanger having a first inlet connected to an extraction point at an intermediate position between the high temperature inlet and low temperature outlet of a turbine heat engine and an outlet connected by a conduit to a second inlet to the turbine between the high and low temperature ends thereof and downstream of the extraction point, hi the recuperator thermodynamic medium vapor from extraction point is in heat exchange relationship with thermodynamic medium conducted from the low temperature exhaust end of the turbine unit through a water cooled condenser and in heat exchange relationship in a refrigerant condenser with a refrigerant flowing in an absorption-refrigeration subsystem.
  • thermodynamic medium leaving the recuperator for return to the turbine is conducted through return conduit in further heat exchange relationship with the refrigerant of the absorbent-refrigerant subsystem and is heated in a heat exchanger by an external source of heat energy and is returned to the high temperature end of the turbine through conduit to complete the cycle.
  • External coolant such as water, is conducted through the thermodynamic-medium condenser in heat exchange relation with the thermodynamic medium passing there through from the low temperature exhaust end of the turbine.
  • U.S. Patent No. 5,537,823 to Vogel discloses a combined cycle thermodynamic heat flow process for the high efficiency conversion of heat energy into mechanical shaft power. This process is particularly useful as a high efficiency energy conversion system for the supply of electrical power (and in appropriate cases thermal services).
  • the high efficiency energy conversion system is also disclosed.
  • a preferred system comprises dual closed Brayton cycle systems, one functioning as a heat engine, the other as a heat pump, with their respective closed working fluid systems being joined at a common indirect heat exchanger.
  • the heat engine preferably is a gas turbine, capable of operating at exceptionally high efficiencies by reason of the ability to reject heat from the expanded turbine working fluid in the common heat exchanger, which is maintained at cryogenic temperatures by the heat pump system.
  • U.S. Patent No. 6,052,997 to Rosenblatt discloses an improved combined cycle low temperature engine system having a circulating expanding turbine medium that is used to recover heat as it transverses it turbine path. The recovery of heat is accomplished by providing a series of heat exchangers and presenting the expanding turbine medium so that it is in heat exchange communication with the circulating refrigerant in the absorption refrigeration cycle.
  • Previously recovery of heat from an absorption refrigeration subsystem was limited to cold condensate returning from the condenser of an ORC turbine on route to its boiler.
  • U.S. Patent No. 7,010,920 to Saranchuk et al discloses a low temperature heat engine that circulates waste heat back through a heat exchanger to the prime mover inlet.
  • the patent discloses a method for producing power to drive a load using a working fluid circulating through a system that includes a prime mover having an inlet and an accumulator containing discharge fluid exiting the prime mover.
  • a stream of heated vaporized fluid is supplied at relatively high pressure to the prime mover inlet and is expanded through the prime mover to a lower pressure discharge side where discharge fluid enters an accumulator.
  • the discharge fluid is vaporized by passing it through an expansion device across a pressure differential to a lower pressure than the pressure at the prime mover discharge side.
  • Vaporized discharge fluid to which heat has been transferred from fluid discharged from the prime mover, can be returned through a compressor and vapor drum to the prime mover inlet.
  • Vaporized discharge fluid can be removed directly from the accumulator by a compressor where it is pressurized slightly above the pressure in the vapor drum, to which it is delivered directly, or it can be passed through a heat exchanger where the heat from the compressed fluid is transferred to an external media after leaving the compressor in route to the vapor drum.
  • Liquid discharge fluid from the accumulator is pumped to a boiler liquid drum, then to the vapor drum through a heat exchanger.
  • the liquid discharge fluid may be expanded through an orifice to extract heat from an external source at heat exchanger and discharged into the vapor drum or the accumulator, depending on its temperature upon leaving heat exchanger.
  • U.S. Patent No. 7,096,665 to Stinger et al discloses a Cascading Closed Loop Cycle (CCLC) and Super Cascading Closed Loop Cycle (Super-CCLC) systems are described for recovering power in the form of mechanical or electrical energy from the waste heat of a steam turbine system.
  • the waste heat from the boiler and steam condenser is recovered by vaporizing propane or other light hydrocarbon fluids in multiple indirect heat exchangers; expanding the vaporized propane in multiple cascading expansion turbines to generate useful power; and condensing to a liquid using a cooling system.
  • the liquid propane is then pressurized with pumps and returned to the indirect heat exchangers to repeat the vaporization, expansion, liquefaction and pressurization cycle in a closed, hermetic process.
  • the system can be utilized to generate
  • the present invention includes an externally heated engine contained within an enclosure.
  • a rotating member is mounted within the enclosure on bearings, with a shaft that extends through a seal, to the outside of the engine.
  • Mounted upon the rotating member are one or more blades.
  • a flow of gasses is directed upon the surface of these blades by the action of one or more stationary nozzles.
  • force is exerted upon the blades. This causes the rotating member to revolve, and torque is exerted upon the shaft while it rotates.
  • a rotating shaft is able to perform work, and this is accomplished by coupling the shaft to an electrical generating device thereby producing electrical power.
  • Very large volumes of useful, moderate pressure gas are produced easily in this invention, at low temperatures, by using a working fluid such as a refrigerant.
  • a working fluid such as a refrigerant.
  • refrigerant Rl 34 is one possible type of working fluid.
  • Many other standard refrigerant types are also suitable.
  • This refrigerant, in its liquid form, will boil very readily at low temperatures and pressures, and produce voluminous amounts of hot gas after being heated.
  • Rl 34 gas is particularly suited for this purpose, and completely avoids the need for high pressures and temperatures.
  • the blades mounted on the rotating member of the instant invention are not of traditional design.
  • Prior art blades tend to be made for either high pressure and temperature gas flows - like in a jet engine for instance - or for flows of liquids, especially water, as in a hydroelectric plant for instance. These blades do not function well for low pressure and temperature gasses.
  • the instant invention overcomes the limits of the prior art by combining a unique blade design with a particular design, to thereby extract power effectively under the desired conditions.
  • the nozzle directs the flow almost straight on to the surface of the blade. This creates a higher pressure on the upstream side of the blade than on the downstream side, and due to this impact effect, the pressure differential, delta P, produces a net force on the blade in the desired direction. Even a few pounds of delta P can produce a large torque if the blade surface area is great enough, and the diameter of the rotating member is large.
  • the blade design additionally takes advantage of the change of momentum in a flow that is produced by the geometry of the blade and the flow of the hot gaseous working fluid. By reversing the flow of working fluid the resulting reaction force on the blade will be large, and in the desired direction.
  • the momentum of a flow of gas is proportional to the square of its velocity, and so the nozzles are designed to greatly accelerate the velocity of the flow, prior to reaching the blade.
  • the force generated by the velocity of the gas flow is a vector quantity, and so a change in direction can be as effective as a change in speed. So, rather than have the flow crash to rest up against the blade surface, the blade surface is curved, and in turn the flow is also turned almost 180 degrees. This produces a momentum change almost double that than if the flow had been brought to rest against the blade.
  • the combination of very high (even supersonic) velocities and radical change in direction result in a very large change in momentum. Thus a large reaction force is exerted on the blade.
  • Figure 1 is an exploded view of the core of the turbine showing the major components, including blades, nozzles, the rotating member, and the enclosure.
  • Figure 2A is a front view of the rotating member with mounting recesses for the blades.
  • Figure 2B is a side view of the rotating member with the mounting recesses for the blades.
  • Figure 3 A is a top view of one of the blades.
  • Figure 3B is a side view of one of the blades
  • Figure 4 shows one end plate, the rotating member, the blades and the nozzles superimposed so that their relationships can be seen.
  • Figure 5A shows one end plate with the nozzles and also the mounting and locating holes for the plate.
  • Figure 5B is a top view of the device shown in Figure 5 A.
  • Figure 6 A is a front view of the center portion, or ring, of the enclosure.
  • Figure 6B is a top view of the center portion or ring shown in figure 6 A
  • Figure 7A is a front view of the opposite end plate with the exhaust ports.
  • Figure 7B is a top view of the opposite end plate with the exhaust ports.
  • Figure 8 shows a converging nozzle, aligned with a blade, and the resulting directions of flow.
  • Figure 9 shows a converging-diverging nozzle, aligned with a blade, and the resulting directions of flow.
  • Figure 1OA is a cross sectional view of the converging nozzle.
  • Figure 1OB is a perspective view of the nozzle of figure 1OA
  • Figure 1 IA is a cross sectional view of the converging-diverging nozzle.
  • Figure 1 IB is a perspective view of the nozzle of figure 1 IA.
  • Figure 12 shows a full system diagram, with a buffering heat exchanger on the input loop, and using a generalized source of waste heat. This would facilitate having a heat pump on the input side, if needed.
  • Figure 13 shows a full system diagram, with a buffering heat exchanger on the input loop, and using a solar array as a source of heat. This would facilitate having a heat pump on the input side, if needed.
  • Figure 14 shows a full system diagram, without a buffering heat exchanger on the input loop, and using a generalized source of waste heat.
  • Figure 15 shows a full system diagram, without a buffering heat exchanger on the input loop, and using a solar array as a source of heat.
  • FIGS 1 through 11 describe the heat engine.
  • Figures 12 through 15 describe the complete thermodynamic system.
  • Figure 1 shows an exploded view of the heat engine components.
  • the heat engine includes a left end bell 6, a right end bell 7, and a ring 4 that act together to enclose, seal, and support the engine.
  • a rotating member 1 is mounted on a shaft 3, and the shaft 3 is supported by bearings 5 that are mounted in both left end bell 6 and right end bell 7.
  • the shaft 3 is operatively connected to an electrical generator or other mechanical device to extract work from the rotating member 1.
  • the left end housing includes inlet ports 16 each supporting a nozzle 8.
  • the right hand bell 7 includes exhaust ports 17. While the invention is illustrated with four inlet nozzles, the number of inlet ports and corresponding nozzles can vary from one to many.
  • the left end bell 6, the ring 4 and right end bell 7 are securely fastened together in a fluid tight relationship with a plurality of fasteners, such as bolts and nuts and seals (not shown).
  • a plurality of fasteners such as bolts and nuts and seals (not shown).
  • Bores 15 circumferentially spaced about the right and left end bells 6 and 7 and ring 4 are sized and configured to allow passage of each of the plurality of bolts,
  • the rotating member 1 has a first planar surface 51 adjacent the left end bell 6 and a second planar surface 53 adjacent the right end bell 7.
  • An outer peripheral surface 55 is contiguous with both the first and second planar surfaces.
  • the blade 2 has a width approximately equal to the distance between the first and second planar surfaces and a height that extends outward from the outer peripheral surface 55.
  • Rotating member 1 has dovetail shaped mounting slots 9 into which the blades 2 may be slid from the side.
  • Blades 2 have a wedge shaped base 10 with mounting holes 13 through which pins and bolts are installed thereby holding the blades in place once they are slid into place in the mounting slots 9. The combined effect is to prevent the blades from being slung away from the rotating member by the forces of rotation, and also to prevent the blades from moving side to side and thus rubbing on the side walls of the enclosure.
  • Each blade 2 has a concave surface 12 on a first side surface of the blade and a convex surface 11 on a second side surface of the blade 2.
  • Figures 1OA and HA show the nozzles in cross section. Gas enters from the left, and is passed through a converging nozzle, as in figure 1 OA, or a converging-diverging nozzle, as in figure HA to achieve a very high gas velocity.
  • the nozzles are each fastened and sealed within their respective inlet ports 16 to facilitate removal and replacement as desired.
  • differing nozzle designs may be used to operate the engine in differing circumstances requiring changes to flow properties.
  • the nozzles are formed as a long slender hollow body which acts to receive the working gases and deliver them to a precise location and flowing in a desired direction.
  • a tapered tip at the exit of the nozzle places the exiting flow into the desired position in the immediate proximity of the blades 2 that are mounted on the rotating member 1.
  • Figure 4 is a perspective view of the left end bell 6, the rotating member 1, the blades 2, and the nozzles 8, all superimposed in a single view.
  • the invention specifically provides a plurality of blades, and a plurality of nozzles, as shown in figures 1 and 4 thereby creating multiple pulses of force to be applied to the rotating element 1 in parallel. An even larger number of force pulses are produced as the rotating member completes a full revolution. Providing multiple pulses in parallel, increases the torque available at a given instant. Providing multiple pulses per revolution increases the power produced per revolution. It is understood that one of ordinary skill in the art could alter the numbers of blades and nozzles, and thus the power available from an engine. The numbers shown are for illustration and are not limiting.
  • Figure 1OA is a cross sectional view of a converging nozzle 8A and figure 1OB is a perspective view of the converging nozzle 8 A.
  • Figure HB is a cross sectional view of a converging-diverging nozzle 8B and figure 1 IB is a perspective view of the converging-diverging nozzle 8B.
  • thermodynamic system as presented in figures 12 through 15. These figures present optional configurations that are possible. Other variations of the basic configuration could be envisioned by one skilled in the art, and these figures are not limiting.
  • thermodynamic loops which make up the system. These are; the outside loop which brings heat from the source, the inside loop which runs the engine directly, and the heat pump loop, which recycles waste heat from the engine back into the system. We describe these in detail below.
  • the outside, or heat source loop begins with heat source 18.
  • This source may be any source of low temperature heat, including waste heat from any number of waste heat sources or solar and geothermal heat sources as well.
  • the external heat source may supply temperatures as low as 250 0 F.
  • heat from the source 18 is conveyed by a first heat transfer fluid around to pump 21.
  • the first heat transfer fluid may be Paratherm NF®, or one of many commercial equivalents.
  • the speed of pump 21 is controlled by control unit 22, to achieve desired pressures and flow rates.
  • a relief valve may be incorporated into the loop to avoid the buildup of damaging excess pressure.
  • the hot heat transfer fluid is then conveyed to heat storage tank 23, where it is held using a phase change material.
  • This material in storage tank 23 changes phase from solid to liquid when heated to the desired temperature.
  • the heat of fusion of such material being very large and capable of holding very large quantities of heat in a small volume.
  • the stored heat may be used at a later time when the external heat source may become temporarily unavailable.
  • Nitrogen tank 20 is used to hold an inert gas such as nitrogen in the tops of the expansion tanks to prevent suction pressures from falling too low and causing pump cavitations, and to prevent corrosion.
  • secondary pump 25 is started. This pump circulates a second heat transfer fluid from the storage tank 23 over to the main heat exchanger 24.
  • Secondary speed controller 26 controls pump 25 and maintains the desired pressures and flow rates.
  • the inside, or turbine loop functions in the following manner.
  • Heat from main heat exchanger 24 is conveyed by the inside, or turbine loop, heat transfer fluid, which is a refrigerant, to the heat engine 27.
  • Heat engine 27 is constructed and operated in the manner disclosed in figures 1 through 11.
  • the refrigerant will operate at low temperatures of less than 300 deg F, and at pressures of less than 200psig.
  • the heat transfer fluid within the turbine loop will condense at temperatures as low as 80 degrees F and will boil at about 70 degrees F when used in this heat engine.
  • This heat engine 27 then operates, and conveys power to generator unit 28.
  • the generator unit 28 produces electricity which is conducted to an inverter 29.
  • the inverter 29 processes the power and makes it available for use externally.
  • the refrigerant leaving heat exchanger 24 is bypassed around the heat engine through orifice 44. This allows the inside loop to warm up, without subjecting the heat engine to cold refrigerant, which would condense and cause problems.
  • the gaseous refrigerant passes into the heat exchanger 30, which serves to condense the gas back to a liquid.
  • heat is released to the heat pump loop, to be discussed presently.
  • the inside loop refrigerant now a liquid, passes through pressure control valve 46, which prevents the pressure from dropping too low which would destabilize the loop function.
  • the refrigerant is then stored in the receiver 45, where it awaits further demand for circulation. Once further fluid is required, it departs the receiver 45 and makes its way through sub-cooler 38, where it is cooled just sufficiently to prevent premature formation of any gas bubbles in the liquid.
  • the flow then continues on to pump 41.
  • the pump acts to raise up the pressure of the liquid to the level required for operation.
  • Flow gauge 42 provides a measure of the rate of flow, which is controlled by the speed of the pump.
  • valve 40 This valve is normally on, but is closed when the engine is off, to prevent flooding of the downstream components.
  • valve 40 On passing through valve 40 the flow reaches heat exchanger 39. Here it picks up reclaimed heat from the heat pump loop to be discussed presently. This raises the temperature of the liquid and causes it to boil and to form a gas. From here, the flow travels back to heat exchanger 24, where it receives the majority of the required heat, and the cycle begins again. The system actually reclaims so much heat that the balance of the heat required to operate the engine comes from heat exchanger 39. Only a small amount of heat is added on each pass around the loop from exchanger 24. This is central to the efficiency of the total system, and is totally unlike prior art engines.
  • liquid heat reclaiming transfer fluid again a refrigerant
  • expansion valve 31 the pressure is dropped sharply, in a controlled manner, and provided to heat exchanger 30.
  • the refrigerant begins to boil, and becomes a very cold gas.
  • This cold gas extracts heat from the inside loop, through heat exchanger 30, and carries away this heat to be reclaimed.
  • the cold gas now travels to pressure control valve 32, where the drop in pressure is regulated.
  • the gas pressure is kept high enough that the gas temperature does not drop to a temperature lower than that which is desired. From there, the gas travels to accumulator 34 where any liquid drops inadvertently remaining are held temporarily, thus preventing them from reaching and damaging the compressor.
  • the flow still a cold gas, then travels to compressor 35.
  • the gas is greatly compressed, reaching much higher levels of pressure and temperature.
  • the flow then travels to heat exchanger 39, where the temperature is now high enough so that the heat may be efficiently reinjected into the inside, or turbine loop process.
  • the heat has been reclaimed, along with the heat resulting from the compression work done by the compressor.
  • the heat pump loop refrigerant gas cools sufficiently that it recondenses to a liquid once again. It then passes through sub- cooler 37 which condenses any remaining liquid and slightly sub-cools the liquid. It then passes through pressure control valve 33 which prevents the pressure from dropping too low and destabilizing the loop function, and then finally returns to receiver 36, where the heat pump loop process begins again.
  • a filter/dryer element is utilized to remove stray particles and also stray moisture from the loop thereby preventing all components from icing, damage and corrosion.
  • system controller and display 43 is provided. This provides automatic control of the entire system, using software created for this purpose. It will be appreciated that a system of this complexity can only be operated in the field under automatic control.
  • Figure 13 is a diagrammatic representation of the power system shown in figure 12 with a buffering heat exchanger on the input loop, substituting a solar array as a source of heat. This would facilitate having a heat pump on the input side, if needed.
  • Figure 14 is a diagrammatic representation of the power system described in figure 12 however in this instance without a buffering heat exchanger on the input loop, and using a generalized source of waste heat.
  • Figure 15 is a system similar to that shown in figure 14 without a buffering heat exchanger on the input loop, and substituting a solar array as a source of heat.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)

Abstract

L'invention porte sur un système de production d'électricité qui comprend une boucle de source de chaleur qui fournit de la chaleur à une boucle de turbine. La chaleur peut être de la chaleur perdue provenant d'une turbine à vapeur, d'un système de traitement industriel ou de réfrigération ou de conditionnement d'air, de collecteurs de chaleur solaire ou de sources géothermiques. La boucle de source de chaleur peut également comprendre un milieu de stockage de chaleur pour permettre un fonctionnement continu même lorsque la source de chaleur est intermittente. Dans la boucle de turbine, un fluide de travail est amené à ébullition, injecté dans la turbine, récupéré à l'état condensé et recyclé. Le système de production d'électricité comprend en outre une boucle de récupération de chaleur comprenant un fluide qui extrait de la chaleur de la boucle de turbine. Le fluide de la boucle de récupération de chaleur est ensuite porté à une température plus élevée puis placé en relation d'échange de chaleur avec le fluide de travail de la boucle de turbine. La turbine comprend une ou plusieurs aubes montées sur un élément rotatif. La turbine comprend également une ou plusieurs buses capables d'introduire le fluide de travail gazeux, à un très petit angle sur la surface de l'aube ou des aubes à une très grande vitesse. Le différentiel de pression entre les surfaces amont et aval de l'aube ainsi que le changement de direction du flux de gaz chaud à grande vitesse créent une force combinée qui communique une rotation à l'élément rotatif.
PCT/US2010/024563 2009-02-20 2010-02-18 Système de production d'électricité thermodynamique WO2010096540A2 (fr)

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EP10705506A EP2399003A2 (fr) 2009-02-20 2010-02-18 Système de production d'électricité thermodynamique
CN2010800081066A CN102405332A (zh) 2009-02-20 2010-02-18 热力能量发生系统

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US15402009P 2009-02-20 2009-02-20
US61/154,020 2009-02-20

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WO2010096540A2 true WO2010096540A2 (fr) 2010-08-26
WO2010096540A3 WO2010096540A3 (fr) 2011-11-24

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9382801B2 (en) 2014-02-26 2016-07-05 General Electric Company Method for removing a rotor bucket from a turbomachine rotor wheel

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2014128600A2 (fr) * 2013-02-21 2014-08-28 Bhanushali Dilip Vasantlal Moteur à injection pour production d'énergie

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US3501249A (en) 1968-06-24 1970-03-17 Westinghouse Electric Corp Side plates for turbine blades
US3822554A (en) 1972-06-26 1974-07-09 F Kelly Heat engine
US3953973A (en) 1974-05-29 1976-05-04 Cheng Chen Yen Heat engine and heat pump utilizing a working medium undergoing solidification and melting operations
US4073069A (en) 1976-08-23 1978-02-14 Megatech Corporation Turbine demonstration
US4292809A (en) 1978-07-24 1981-10-06 AB Svenska Flacktfabriken, Fack Procedure for converting low-grade thermal energy into mechanical energy in a turbine for further utilization and plant for implementing the procedure
US4421454A (en) 1979-09-27 1983-12-20 Solar Turbines Incorporated Turbines
US4475343A (en) 1980-05-14 1984-10-09 Bercwerksverband GmbH Method for the generation of heat using a heat pump, particularly for _processes run only at high temperatures
US4400137A (en) 1980-12-29 1983-08-23 Elliott Turbomachinery Co., Inc. Rotor assembly and methods for securing a rotor blade therewithin and removing a rotor blade therefrom
US4502838A (en) 1982-06-21 1985-03-05 Elliott Turbomachinery Co., Inc. Solid wheel turbine
US4503682A (en) 1982-07-21 1985-03-12 Synthetic Sink Low temperature engine system
US5074754A (en) 1990-04-23 1991-12-24 United Technologies Corporation Rotor blade retention system
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US5537823A (en) 1994-10-21 1996-07-23 Vogel; Richard H. High efficiency energy conversion system
US6052997A (en) 1998-09-03 2000-04-25 Rosenblatt; Joel H. Reheat cycle for a sub-ambient turbine system
US7096665B2 (en) 2002-07-22 2006-08-29 Wow Energies, Inc. Cascading closed loop cycle power generation
US7010920B2 (en) 2002-12-26 2006-03-14 Terran Technologies, Inc. Low temperature heat engine

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9382801B2 (en) 2014-02-26 2016-07-05 General Electric Company Method for removing a rotor bucket from a turbomachine rotor wheel

Also Published As

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WO2010096540A3 (fr) 2011-11-24
EP2399003A2 (fr) 2011-12-28
CN102405332A (zh) 2012-04-04
TW201040380A (en) 2010-11-16

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