Heat pump engine

Abstract

Disclosed in the present invention is a heat pump engine, capable of converting the internal energy of atmosphere or seawater absorbed by a low-boiling-point refrigerant into the kinetic energy to drive a propeller and a generator. A high-pressure liquid refrigerant undergoes throttling and pressure reduction by means of a throttle valve, and then enters an evaporation pipe to absorb heat of an environmental heat source; the refrigerant undergoes evaporation and expansion, and then is drawn by a compressor into a heat exchange chamber to absorb heat of a radiator pipe inside the heat exchange chamber; the refrigerant further undergoes heating and expansion and then impacts a turbine to do work; the refrigerant having done work is drawn into the compressor and releases latent heat to condense back into a liquid; the condensed refrigerant impacts a small turbine inside a compressor hub; and then the refrigerant flows back to the throttle valve through a liquid flow core pipe. In a continuous cycle, the turbine drives the compressor, propeller, and generator.

Description

Heat pump engine TECHNICAL FIELD

[0001] The present application relates to the technical field of heat pump engine, in particular to a heat pump engine which is coupled with heat pump technology and aero-engine technology. BACKGROUND

[0002] As the energy necessary for human survival and development, usually manifested as heat, mechanical energy, electromagnetic energy, they can be converted into each other, and the use of electricity is the most widely used. In addition to the light energy from the sun and the wind energy, the mechanical energy of water and the chemical energy of plants, etc., which can be converted into electricity by solar panels and wind turbines, water turbines and generators, the fossil energy from the earth's crust, such as gasoline, kerosene, diesel, heavy oil and oil gas, etc., as shown in FIG. 3, can be converted into heat energy by gasoline engine, gas turbine, diesel engine and boiler steam turbine, and further converted into mechanical energy or electricity. Coal and nuclear fuel provide heat for thermal power plants and nuclear power plants, which can be converted into electricity. These energy sources have their own advantages, but more are their own difficulties and disadvantages, such as the need for multiple equipment, complex production process, low conversion efficiency, environmental pollution, climate warming, especially high cost, etc.

[0003] The present application provides a single heat source heat engine in the sense of thermodynamics - heat pump engine, which can convert the internal energy of the atmosphere and seawater into kinetic energy to drive the propeller and generator, and can end the history of fossil energy.

[0004] SUMMARY

[0005] The purpose of the present application is to provide a heat pump engine to solve the problems raised in the background.

[0006] To solve the above technical problems, the present application provides the following technical scheme:

[0007] The heat pump engine of the present application is surrounded by a multi-stage impeller compressor, and the straight conical surface cylinder shell of the compressor is the rotor of the turbine and the power output cylinder shaft, the turbine outlet is folded back to the center, which is the inlet of the compressor, which is beneficial to the recovery of compression heat and the compact and reasonable layout of the whole structure; comprising:

[0008] The main shaft is connected with the straight conical surface cylinder slender neck in the form of inner and outer spline, and the main shaft is connected with the main shaft front bearing in the form of thread; the high-pressure dynamic sealing ring behind the main shaft front bearing blocks the high-pressure liquid flow of the liquid collecting ring chamber;

[0009] The head cone fairing is fixed as a whole with the inlet guard and the outer ring, covers the front end of the two semicircular barrel-shaped shields and is fixed with screws, and the shield is fastened with edge strips by bolts;

[0010] The front propeller, the rear propeller, the blades and the hubs are integrated as a whole, and are bolted to the front and rear of the main shaft;

[0011] The front generator and the plenum are separated by the front cabin base,

[0012] The front supports between the shroud and the main body are fused together with the front end of the front section of the main body shell, and the axial view of each support is radially arranged and consistent with the direction and number of the evaporation pipes radially extending on the outer wall of the plenum; the outer periphery of each support is fused with a rim that can be attached to the corresponding part of the shroud, and is screwed to the inner side of the shroud; the front and rear edges of each support are blade-shaped, thick in the middle, and the rear edge is fixed with a rib in front of the evaporation pipe by a bolt and nut;

[0013] Each evaporation pipe is longitudinally placed and radially arranged, and the front and rear ends are loosely assembled, the front end is curved towards the center and integrated with a nearly circular truncated cone ring cylinder that closely fits the outer wall of the front section of the main body shell, and is screwed to the outer wall of the front section of the main body shell; the tail end of each evaporation pipe is fastened by a nut on the tail seat with external threads; the main body shell surrounded by each evaporation pipe is divided into two sections; the inner side of the front end of the front section is screwed to the front cabin base; the rear end and the front end of the rear section are screwed to the hollow shell of the compressor stator; the inner side of the rear end of the rear section is screwed to the rear cabin base;

[0014] The liquid flow core pipe extends from the front end of each evaporation pipe, passes through the plenum, and is screwed into the inner wall of the ring chamber with a center through screw; the liquid flow hole is connected to the liquid collection ring chamber at the outlet of the small turbine, and a suitable amount of radial tripod support is fixed on each liquid flow core pipe to keep the liquid flow core pipe centered in the evaporation pipe; the end of each liquid flow core pipe is fastened to the regulating valve with a center through screw against the pipe end flange in the rear support;

[0015] The front and rear edges of each support are blade-shaped, thick in the middle, and the rear support is opened and capped with a screw on the same side at the middle rear position, and the hollow support has a row of tail seats and regulating valves for easy assembly and maintenance;

[0016] The heat exchange chamber radiator is fixed to the outside of the straight fluted conical cylinder neck in the form of splines, and is resisted by the stator of the small turbine fixed to the outside of the slender neck of the straight fluted conical cylinder in the form of splines;

[0017] The base has supports that support and integrate the radiator at the inlet and outlet ends of the heat exchange chamber;

[0018] The radiator is screwed into the base with a center through bolt against the pipe end flange at the outlet end of the heat exchange chamber to connect the orifice of the compressor outlet; it is also screwed into the base in the same way at the inlet end of the heat exchange chamber to connect the orifice of the small turbine inlet;

[0019] The compressor rotor, the rear end of the hub is constrained to the radiator base with high pressure dynamic seal ring with sliding bearing; the front end is also constrained to the inner wall of the gas ring chamber with high pressure dynamic seal ring with sliding bearing;

[0020] The stern nozzle with jet flow guide groove and the outlet grille and the stern cone whole cover are integrated, the front end covers the rear end of the two half barrel-shaped shroud and is fastened with screws;

[0021] The compressor inner rotor, the front end of the cylinder shaft is connected to the inner side of the straight-line conical throat with high pressure dynamic seal ring; the rear end is connected to the main shaft with conical roller bearing, the outer end is fixed to the sun gear of the planetary gear, and the inner end supports the large end bearing of the straight-line conical cylinder;

[0022] The ring gear of the planetary gear, the ring gear is fixed to the rear section of the main shaft with spline form; the front end of the front end of the main shaft is fixed to the ring gear with internal thread; the ring gear of the planetary gear is supported on the main shaft with the bearing sleeve and is pressed against the main shaft;

[0023] The separated centripetal inner volute backflow chamber, the front cabin separation base is fixed to the front end of the front section of the main body shell, and the front end is loaded on the main shaft front bearing, and then the front generator is loaded, and the front end cover is fixed to the front cabin separation base with screws; the front end cover is loaded with the propeller shaft seal ring, and the seal ring cover is fixed to the front end cover with screws; the front propeller is fastened to the front end of the main shaft with a washer nut;

[0024] The rear cabin separation base separates the centripetal inner volute backflow chamber and the rear start-up generator integrated machine chamber; the rear cabin separation base is fixed to the rear end of the rear section of the main body shell, and then the planetary gear is loaded, and the planetary gear is fixed to the rear cabin separation base with screws, the ring gear hub is fixed to the main shaft with spline form, the rear start-up generator integrated machine is loaded, the stator seat is fixed to the rear cabin separation base with screws, and the bearing inner ring is constrained to the main shaft with the stop washer ring; the stop washer ring fixed to the main shaft constrains the bearing and the ring gear hub; the rear end cover with the propeller shaft seal ring is fixed to the rear cabin separation base with screws, and the seal ring cover is fixed to the rear end cover with screws; the rear propeller is fastened to the rear end of the main shaft through the washer nut;

[0025] The main shaft outer sleeve shaft end head and the rear cabin separation base are provided with a seal ring to separate the centripetal inner volute backflow chamber, the planetary gear chamber, and the start-up generator integrated machine chamber;

[0026] The rear support and the outer periphery of the rear cabin separation base are fused together and are evenly distributed in a radial manner, and are consistent with the longitudinally arranged evaporation pipes; the outer periphery is also fused with a rim that can be attached to the corresponding part of the shroud, and is fixed to the inner side of the shroud with screws;

[0027] All the blades of the impeller and the hub or the rim are integrally machined, and the hub or the rim is fixedly connected to the corresponding part with spline form.

[0028] As an improvement, the power machine includes several temperature, pressure, and rotating speed sensors, and an electronic control system which is self-destroyed when being disassembled or moved.

[0029] The present application adopts the following key measures:

[0030] I. The multi-stage impeller compressor is surrounded by a multi-stage impeller turbine, and the straight conical surface cylindrical shell of the compressor is also the rotor of the turbine and the power output cylinder shaft, which is beneficial to the recovery of compression heat.

[0031] II. There is a multi-stage impeller compressor between the gas collection chamber and the turbine, which blocks the top of the gaseous refrigerant at the turbine outlet after the compression heat is recovered, and makes the evaporating pipe outside the throttle valve be in a low-pressure and low-temperature state easy to evaporate and absorb heat.

[0032] III. A heat exchange chamber is arranged between the compressor and the turbine, and the high-pressure and high-temperature refrigerant at the outlet of the straight conical surface cylindrical throat neck part releases latent heat through the radiator in the heat exchange chamber and condenses back to liquid state.

[0033] IV. The straight conical surface cylinder is not only the power output shaft of the turbine, but also the outer shell rotor of the compressor with embedded multi-stage impellers. The multi-stage impellers on the outer shell rotor and the multi-stage impellers on the main shaft are alternately arranged and counter-rotated, which greatly improves the compression efficiency.

[0034] V. A small turbine is arranged between the compressor hub and the slender neck part of the straight conical surface cylinder, which is impelled by the high-pressure liquid flow from the outlet of the radiator. The stator is fixed to the outside of the slender neck part, and the rotor is fixed to the inside of the compressor hub. The small turbine not only recovers part of the compression energy of the high-pressure refrigerant condensed back to liquid state, but also makes the compressor rotate faster on the basis of the rotating speed of the turbine, and has higher efficiency.

[0035] The heat pump engine is different from existing internal combustion engines, external combustion engines, steam turbines and other power machines. It does not consume any fuel, only needs water from rivers, lakes, seas and atmosphere with not too low temperature as heat source, can convert most of the internal energy of the water from rivers, lakes, seas and atmosphere absorbed by the low-boiling-point refrigerant into mechanical energy to drive the propeller and the generator, and has no "waste" heat discharged to the low-temperature heat source, thereby becoming a brand-new generator set or boat propulsion power machine.

[0036] Compared with the internal combustion engine providing mechanical energy, the electric motor provides mechanical energy, which is cleaner and more convenient. Compared with photovoltaic power generation, wind power and hydroelectric power, the application is less affected by climate, environment and geographical location, and is more stable in power supply, high efficiency and low cost. Compared with coal-fired boiler, oil(gas) boiler, nuclear reactor boiler and steam turbine generator set, the application has compact and exquisite structure, small floor area, easy installation, does not consume any fuel, provides cheap, abundant and simple electric energy. Compared with the nuclear power of the ship, the power unit of the application has compact and light structure, and does not occupy the cabin space and worry about nuclear radiation pollution, and the operation cost is low. Compared with the diesel engine and gas turbine power of the surface ship, the application has compact and light structure, which can be hoisted under the waterline of the stern, not only does not occupy the cabin space, but also does not need to carry fuel, the power cost is greatly reduced, and the endurance is comparable to nuclear power. Compared with the diesel-electric power of the submarine, the power of the application is much better. As the power of the helium airship in the airspace where the atmospheric temperature is not too low, compared with photovoltaic power generation, battery, electric motor power and gasoline engine power, the application is more stable and durable, and if it always flies in the low-altitude airspace in the middle and low latitudes, the endurance is comparable to nuclear power, and it is cheap and much safer. BRIEF DESCRIPTION OF DRAWINGS

[0037] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the following will briefly introduce the drawings needed to be used in the embodiments or prior art description. Obviously, the drawings listed below only show some structural schematic diagrams of the present application, but not all.

[0038] Fig. 1 is a structural schematic diagram of a heat pump engine of the present application.

[0039] Fig. 2 is an embodiment diagram of a heat pump engine of the present application.

[0040] Fig. 3 is a background technology diagram of a heat pump engine of the present application.

[0041] Reference signs:

[0042] nose cone fairing 1; front propeller 2; front generator 3; front bulkhead 4; front strut 5; evaporator tube 6; liquid flow core tube 7; compressor rotor 8; compressor stator 9; high pressure dynamic seal 10; compressor stator hollow shell 11; radiator 12; turbine stator 13; turbine rotor 14; straight fluted conical bearing 15; main shaft outer sleeve bearing 16; rear bulkhead 17; planetary gear carrier 18; main shaft rear bearing 19; stringer 20; rear propeller 21; propeller shaft seal 22; stern nozzle 23; inlet screen 24; propeller shaft seal 25; front generator 26; main shaft front bearing 27; high pressure dynamic seal 28; liquid collection ring chamber 29; gas collection chamber 30; high pressure dynamic seal 31; small turbine 32; high pressure dynamic seal 33; compressor outlet 34; main shaft 35; compressor outer rotor 36; compressor inner rotor 37; inwardly centripetal volute backflow chamber 38; seal 39; sun gear 40; ring gear 41; generator unit 42; generator unit 43; rear strut 44; outlet screen 45; stern cone fairing 46; DETAILED DESCRIPTION

[0043] The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all the embodiments of the present application. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative work fall within the protection scope of the present application.

[0044] In the description of the embodiments of the present application, it should be noted that if the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer" and the like appear, the indicated orientation or positional relationship is based on the orientation or positional relationship shown in the drawings or the orientation or positional relationship commonly used when the product of the present application is used, and is only for the convenience of describing the present application and simplifying the description, and therefore cannot be understood as indicating or implying that the indicated device or element must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as limiting the present application.

[0045] In addition, if the terms "first", "second", "third" and the like appear, they are only used for differentiation in description and cannot be understood as indicating or implying relative importance. If the terms "horizontal", "vertical", "suspension" and the like appear, they do not mean that the component must be absolutely horizontal or suspended, but can be slightly inclined. For example, "horizontal" only means that its direction is relatively more horizontal than "vertical", and does not mean that the structure must be completely horizontal, but can be slightly inclined.

[0046] In the description of the embodiments of the present application, if the terms "a plurality of", "several" appear, they represent at least two.

[0047] In the description of the embodiments of the present application, it also needs to be explained that, unless otherwise explicitly specified and limited, if the terms "arrange", "install", "connect", "connect" appear, they should be understood in a broad sense, for example, it can be fixedly connected, or it can be detachably connected, or integrally connected; it can be mechanically connected, or it can be electrically connected; it can be directly connected, or it can be indirectly connected through an intermediate medium, or it can be the communication inside two elements. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0048] The present embodiment combines FIG. 1 to FIG. 2 to explain in detail a heat pump engine.

[0049] The main shaft 35 is connected with the straight conical surface cylinder slender neck in the form of inner and outer splines, and the main shaft 35 is connected with the front shaft bearing 27 in the form of threads; the rear of the front shaft bearing 27 has a high-pressure dynamic sealing ring 28 to block the high-pressure liquid flow of the liquid collecting ring chamber 29;

[0050] The main shaft is a stepped shaft with a front section (combined with the inner spline of the straight conical surface cylinder slender neck with the outer spline to be fixedly connected) gradually thinning from the front to the rear;

[0051] The head cone fairing 1 is fixedly integrated with the inlet guard 24 and the outer ring, covers the front end of the two half-cylinder-shaped fairings, and is fixed by screws. The fairing is fastened by the edge strip 20 with bolts;

[0052] The front propeller 2 and the rear propeller 21 are integrally connected with the hub of the blades and the main shaft 35 by bolts;

[0053] The front generator 3 and the gas collecting chamber 30 are separated by the front cabin partition base,

[0054] The front supports 5 fixedly connected between the fairing and the main body are fused together with the outer side of the front end of the front section of the main body shell, the axial view of each support is radially arranged and consistent with the direction and number of the evaporation pipes 6 radially extending on the outer wall of the gas collecting chamber 30; the outer periphery of each support is fused with a rim that can be attached to the corresponding part of the fairing, and is fixed to the inner side of the fairing by screws; the front and rear edges of each support are blade-shaped, thick in the middle, and the rear edge is fixed with the rib of the evaporation pipe 6 by bolts and nuts;

[0055] Each evaporation pipe 6 is longitudinally placed and radially arranged, and the front and rear ends are loose before assembly. The front end is curved towards the center and integrally fused with the nearly circular truncated cone ring cylinder that closely fits the outer wall of the front section of the main body shell, and is fixed to the outer wall of the front section of the main body shell by screws. The tail end of each evaporation pipe 6 is fastened by the nut on the tail seat 44 with external threads; the main body shell surrounded by each evaporation pipe 6 is divided into two sections; the inner side of the front end of the front section is fixed to the front cabin partition base by screws; the rear end and the front end of the rear section are fixed to the hollow outer shell of the compressor stator 9 by screws; the inner side of the rear end of the rear section is fixed to the rear cabin partition base by screws;

[0056] Liquid flow core pipes 7, each liquid flow core pipe 7 extends from the front end of each evaporation pipe through the gas collecting chamber 30 to screw into the corresponding liquid flow hole on the inner wall of the gas collecting ring chamber 30; the liquid flow holes are all connected to the liquid collecting ring chamber 29 at the outlet of the small turbine 32, and a proper amount of radial tripod support is fixed on each liquid flow core pipe 7 to keep the liquid flow core pipe 7 always centered in the evaporation pipe 6; the end of each liquid flow core pipe 7 is fastened to the regulating valve by screwing against the pipe end flange in the rear support 44;

[0057] The front and rear edges of each support are sharp, the middle is thick, and the rear support is opened at the middle rear part and is fixed by screwing a cover; since each hollow support has a row of tail seats of each evaporation pipe 6 and a regulating valve, it is convenient for assembly and maintenance;

[0058] The heat exchange chamber radiator 12 is fixed to the base outside the straight fluted conical cylinder neck by spline, and is resisted by the stator of the small turbine 32 fixed to the small turbine 32 outside the slender neck of the straight fluted conical cylinder by spline;

[0059] The base has supports supporting the radiator 12 at the inlet and outlet ends of the heat exchange chamber and is integrated with the base;

[0060] The radiator 12 is screwed into the base at the outlet end of the heat exchange chamber by medium penetration bolt against the pipe end flange to connect the orifice of the compressor outlet 34; in the same way, it is screwed into the base at the inlet end of the heat exchange chamber to connect the orifice of the inlet of the small turbine 32;

[0061] The compressor rotor 8 has its hub rear end constrained on the base of the radiator 12 by high pressure dynamic sealing ring 33 with sliding bearing; the front end is also constrained inside the inner wall of the gas collecting ring chamber 30 by high pressure dynamic sealing ring 31 with sliding bearing;

[0062] The stern nozzle 23 with jet flow guide groove, the outlet guard 45 and the stern cone whole cover 46 are integrated, the front end covers the rear end of the two half barrel-shaped guards and is fastened by screw;

[0063] The front end of the cylinder shaft of the compressor inner rotor 37 is connected with the inside of the throat of the straight fluted conical cylinder by high pressure dynamic sealing ring 10 with sliding bearing; the rear end is connected with the main shaft 35 by conical roller bearing, the sun gear 40 of the planetary gear is fixed outside the end, and the straight fluted conical cylinder large port end bearing 15 is supported inside the end;

[0064] The ring gear 41 of the planetary gear is fixed to the rear section of the main shaft 35 by spline; the front end of the start power integrated machine 42 is fixed to the ring gear 41 by internal thread; the ring gear 41 of the planetary gear has the main shaft sleeve shaft end bearing 16 on the main shaft 35 and is resisted by it;

[0065] The centrifugal reflux chamber 38 is separated from the rear compartment base by the rear compartment base, which is fixed to the front end of the main body shell. The front compartment base is fixed to the front end of the main body shell. The front end cover is fixed to the front compartment base by screws. The propeller shaft sealing ring 25 is installed on the front end cover. The front propeller is fastened to the front end of the main shaft by a washer nut.

[0066] The rear compartment base is fixed to the rear end of the main body shell. The planetary gear 18 and 40 are installed on the rear compartment base. The planetary gear 18 is fixed to the rear compartment base by screws. The gear ring hub is fixed to the main shaft 35 by spline. The rear starting and generating integrated machine 42 and 43 is installed. The seat of the starting and generating integrated machine 43 is fixed to the rear compartment base by screws. The stator 43 is also the seat of the rear shaft bearing 19. The inner ring of the bearing 19 is constrained on the main shaft 35 by a retainer washer. The retainer washer is fixed to the main shaft by threads, which constrains the bearing 19 and the gear ring 41 hub. The rear end cover with propeller shaft sealing ring 22 is fixed to the rear compartment base by screws. The sealing ring cover is fixed to the rear end cover by screws. The rear propeller 21 is fastened to the rear end of the main shaft 35 by a washer nut.

[0067] The sealing ring 39 is provided between the main shaft sleeve and the rear compartment base to separate the centrifugal reflux chamber 38, the planetary gear 18 and 40 chamber, and the starting and generating integrated machine 42 and 43 chamber.

[0068] The rear support 44 is fused with the outer periphery of the rear compartment base and is evenly distributed radially. It is consistent with the longitudinally arranged evaporative tube 6. The outer periphery also fuses a wheel rim that can be attached to the corresponding part of the shroud. It is also fixed to the inside of the shroud by screws.

[0069] All the blades of the impeller and the hub or the wheel rim 9, 13, 14, 36, 37 are integrally machined. The hub or the wheel rim is fixed to the corresponding part by spline.

[0070] The power machine includes several temperature, pressure, and speed sensors, as well as an electronic control system that prevents private disassembly and relocation and self-destructs. The self-destructive explosive is installed in the front 4 of the compartment base, the hollow shell of the compressor stator, and the rear 17 of the compartment base.

[0071] In the specific implementation, the low-boiling-point refrigerant is sealed in the closed circulation flow path of "evaporator - gas collector - compressor - heat exchange chamber - turbine - centripetal folding return chamber - compressor - heat exchanger in the heat sink - high-pressure liquid turbine driving compressor - liquid collector - liquid core pipe in the center of each evaporation pipe - tail valve - evaporator", and the evaporator is immersed in the water of rivers, lakes and seas or the atmosphere with a general temperature not lower than 0℃.

[0072] The compressor compresses the gaseous refrigerant at room temperature and low pressure into a liquid state, which is cooled by the heat sink in the center of the heat exchange chamber, and then impacts the small turbine driving the compressor to release part of the pressure energy into the liquid collector, and then flows into the liquid core pipe of each evaporator in the four walls to the throttle valve, and then enters the evaporation pipe after throttling and pressure reduction, and then vaporizes, expands and pressurizes after absorbing the heat energy of the external heat source introduced by the pipe wall, and then flows into the gas collector and is pressed into the heat exchange chamber by the compressor to absorb the heat release of the condensed refrigerant in the heat sink to further increase the temperature, pressure and expansion, and then impacts the (main) turbine rotor, and absorbs the heat release of the compressor introduced through the blades and shaft at the same time, thereby obtaining more rotational kinetic energy.

[0073] The turbine rotation drives the compressor and main shaft rotation, the main shaft drives the propeller and generator, and at the same time, the planet gear drives the counter-rotating impeller of the alternately arranged compressor to reverse at double speed to enhance the compression efficiency. Most of the mechanical energy consumed by the compressor is converted into condensed heat release, a small part of which impacts the small turbine of the compressor at high speed to rotate, and at the same time, a low-pressure area is formed at the outlet of the main turbine, so that the main turbine obtains more rotational kinetic energy.

[0074] Take a 50MW / ship power unit as an example: as shown in Figure 2.

[0075] In order to enable the refrigerant to continuously absorb heat, evaporate, expand, recover condensed heat, further expand, pressurize, work, and then be compressed back to liquid state to flow back to the evaporator for circulation, thereby continuously outputting power, the refrigerant should be sealed in the closed circulation flow path, the working machine must be a multi-stage impeller turbine, the compressor and the compressor must also be multi-stage impeller, and the compressor must be placed in the center of the turbine and be completely surrounded by the straight-line conical cylindrical shell, which is used as the inner shell of the turbine and the conical cylindrical shaft, and also as the conical cylindrical shell of the compressor, so as to facilitate the recovery of condensed heat, which is the key.

[0076] The turbine housing is a cylindrical column, which is the middle section of the main housing, extending forward and backward to the front and rear nearly circular cone-shaped housing, and together with the front and rear conical fairing to form a shuttle-shaped streamline body. The evaporator pipes of the evaporator, which absorbs the internal energy of the environmental heat source, are arranged around the main body and surrounded by a protective cover shaped like a waist drum, and the inlet and outlet are equipped with grilles. The environmental heat source is sucked into the inlet grille by the front propeller, flows through the outer surface of the evaporator pipe, is cooled by heat absorption, is squeezed and accelerated by the gradually converging flow channel, and is driven by the tail propeller to be sprayed out of the outlet grille.

[0077] The outer wall of the straight-line conical cylinder in the main body is fixedly connected with the multi-stage impeller of the turbine rotor, which is alternately arranged with the stator guide vane fixedly connected to the inner wall of the main housing. The axis of the straight-line conical cylinder is provided with a main shaft penetrating through the front and back, and the neck part of the conical cylinder is fixedly connected with a conical top cylindrical sleeve.

[0078] The inner wall of the conical cylinder is fixedly connected with the multi-stage impeller of the compressor, which is alternately arranged with the multi-stage impeller of the compressor fixedly connected to the outer wall of the main shaft sleeve. The inside and outside of the bell mouth of the conical cylinder are the inlet of the compressor and the outlet of the turbine respectively. The outlet turns into the inlet, and the gaseous refrigerant is folded back 180 degrees to the return chamber or the inner volute chamber.

[0079] The neck part of the straight-line conical cylinder is tightly held by the cylindrical sleeve, leaving a gap between the front of the main shaft and the main shaft. The ring groove is the outlet of the compressor, and the many holes around the cylindrical sleeve are fixedly connected to the radiating pipes of the radiator, and the other end of each radiating pipe is open to the inlet of the small turbine of the driving compressor.

[0080] The heat exchange chamber with the radiator is axially arranged in front of the compressor and the turbine. This layout is the key two, that is, the compressor is necessary, the heat exchange chamber is necessary, and the existence of the compressor can make the gaseous refrigerant, which has been fully recovered and condensed heat, increase in temperature and pressure when it enters the heat exchange chamber, and does not cause top support to the upstream, so that the refrigerant after the regulating valve can be more smoothly evaporated at low pressure. At the same time, the refrigerant must release the latent heat in the radiator before flowing back to the evaporator.

[0081] The multi-stage driving impeller of the compressor, i.e. the rotor, is respectively sleeved in the outer wall of the front cabin separation base liquid chamber and the radiator base with bearing high-pressure dynamic sealing ring at the front and rear ends of the hub, and is driven by the small turbine driven by the high-pressure liquid flow from the radiator. The corresponding alternately arranged multi-stage guide vane is fixedly connected to the hollow stator shell on the inner wall of the main housing. The compressor is accelerated in rotation by the small turbine driven by the high-pressure liquid flow on the basis of the main turbine, and its compression efficiency is greatly improved, and the liquid flow pressure energy is partially recovered, which is the key three.

[0082] The gaseous refrigerant, which has absorbed heat from the ambient heat source, is collected in the plenum chamber ahead of the compressor inlet and is then distributed to the evenly distributed evaporator tubes on the periphery of the ring wall. At the same time, the liquid flow core tubes in the center of the evaporator tubes pass through the ring-shaped plenum chamber and are connected to the annular liquid collection chamber at the outlet of the small turbine in the inner wall of the center.

[0083] The front compartment base separates the front generator chamber from the main shaft and the plenum chamber. The main shaft passes through the sealing ring in the center, is then fixed by the anti-backout pin ring, and enters the front generator chamber to fix the generator rotor after being constrained by the bearing. Continue to move forward through the center sealing chamber of the circular cone-shaped main body shell to fix the front propeller. The hub is a smaller circular cone, together with the pointed cone-shaped fairing in the center of the inlet guard, forming the front section of the pointed cone-shaped streamline body.

[0084] The front support on the periphery of the main body shell at the front compartment base supports the front end of the evaporator and supports the front part of the shroud. The inner volute backflow chamber rear wall along the main shaft is the rear compartment base that separates the inner volute backflow chamber from the rear generator chamber. If the main function of the machine is ship propulsion power, the rear compartment base on the periphery of the main body shell also supports the tail end of the evaporator tubes of the evaporator and supports the rear part of the shroud. If the main function is only power generation, the rear support is the rear outlet guard, and the central pointed cone-shaped fairing is also part of the main body shell, that is, the fixed tail cone. At the same time, the rear section of the shroud does not need to be constricted to force the flow of the heat source to accelerate to obtain the thrust.

[0085] The main shaft and its outer sleeve shaft pass through the rear compartment base and are constrained by the bearing therein. The sleeve shaft is fixed to the sun gear of the planetary gear fixed to the compartment base, and the main shaft is fixed to the gear ring of the planetary gear after passing through the sun gear. The alternately arranged compressor impellers fixed to the outer wall of the sleeve shaft and the inner wall of the straight conical tube greatly improve the compression efficiency. This is the key four.

[0086] The main shaft continues to extend rearward in the rear generator chamber outside the gear ring of the planetary gear, fixing the rotor of the power generation and starting integrated machine. If the single-source heat engine is the main function of ship propulsion power, the main shaft passes through the sealing chamber in the center of the circular cone-shaped tail end of the main body shell to fix the rear propeller. The rear section of the main body shell, together with the fairing in the center of the hub and the outlet guard, forms the rear section of the two-tipped fusiform streamline body. If the main function of the machine is only power generation, the rear propeller is cancelled, the outlet guard is the rear support that supports the tail end of the evaporator tube and supports the rear part of the shroud, and the pointed cone-shaped fairing is also part of the main body shell, that is, the tail cone. The heat source flow cross section between the main body and the shroud does not need to be constricted, and it does not need to be forced to accelerate to obtain the thrust.

[0087] The single-source heat engine of the present application is similar in appearance to a turbojet engine without afterburner. It has a waist-drum-shaped protective cover with openings in front and back and is equipped with a front and back support. Inside the protective cover is a streamlined main body with a barrel-shaped middle section and tapered ends, which is coaxial with the protective cover and maintains a proper distance from the cover to allow ambient heat source to flow through and heat the annular longitudinal low-boiling refrigerant evaporation pipes. The front ends of all evaporation pipes are bent inward and fixed to the outer wall of the annular gas collection chamber and are connected to the front support by a rib plate. The refrigerant liquid flow core pipe at the center of each evaporation pipe extends into the liquid collection chamber at the outlet of the small turbine driven by the high-pressure liquid flow of the driving compressor rotating in the annular gas collection chamber. The liquid flow core pipe extends along the axis of the evaporation pipe to the rear end, where it is connected to the regulating valve. The rear end of the evaporation pipe is connected to the rear support. The front and rear supports connect the main body and the protective cover into a whole. Inside the main body connected to the front and rear supports is a front and back cabin partition base, which divides the main body into three sections. The front cabin contains the main generator, the middle cabin contains the annular gas collection chamber and the annular liquid collection chamber, the compressor and the small turbine driven by the compressor. The heat exchange chamber, the radiator inside the heat exchange chamber, the turbine, the compressor, the inner return flow chamber with the turbine outlet 180 degrees inwardly folded back to the compressor inlet, and the generator-starting integrated machine in the back cabin are all connected to the main shaft. The driven spline shaft of the clutch is connected to the rear propeller, and the driving spline hub is connected to the tail end of the main shaft. The main shaft is connected to the generator-starting integrated machine rotor in front, the planet gear ring is connected to the planet carrier on the back cabin partition base, the sleeve shaft is connected to the sun gear at one end and is stopped at the neck of the straight taper cylinder at the other end, which is also the power output shaft of the main turbine and the slender neck of the straight taper cylinder of the compressor housing, and then it passes through the front cabin partition base and is constrained by the bearing in the base to connect the front cabin generator rotor, and then it passes through the front sealing chamber and is finally connected to the front propeller. The outer wall of the straight taper cylinder is connected to the multi-stage turbine impeller, which is alternately arranged with the static (guide) impeller connected to the inner wall of the main body shell. The inner wall of the taper cylinder is connected to the multi-stage impeller of the compressor, which is alternately arranged with the counter-rotating multi-stage impeller connected to the outer sleeve shaft of the main shaft. The inlet end of each liquid flow pipe of the radiator in the heat exchange chamber before the turbine is connected to the neck of the straight taper cylinder and the outlet end is connected to the inlet of the small turbine driven by the compressor hub. The small turbine is located outside the slender neck of the straight taper cylinder connected to the main shaft, the guide impeller is connected to the outer wall of the slender neck, and the alternating dynamic impeller is connected to the inner wall of the compressor hub. The rear end of the compressor hub is constrained by the one-way bearing and high-pressure dynamic seal ring on the radiator base outside the neck of the taper cylinder, and the front section is constrained by the bearing and high-pressure dynamic seal ring on the outer wall of the liquid collection chamber in the front cabin partition base. The small turbine is connected to the high-pressure jet of the radiator at the inlet and is connected to the liquid collection chamber at the outlet. The liquid collection chamber is connected to the liquid flow core pipe at the center of each evaporation pipe through the front cabin partition base and the front support.

[0088] Thus, when starting, the required power supply is connected to the starting motor, and at the same time, the liquid refrigerant is injected from the storage tank to the collecting chamber. The liquid refrigerant, under the drive of the compressor, enters the liquid flow core tube at the center of the evaporating pipe, and after the end control valve controls the release, absorbs the heat of the environmental heat source transmitted by the evaporating pipe wall, evaporates and expands to the gas collecting chamber, and further pressurizes by the compressor to the heat exchange chamber, absorbs the heat of the heat dissipation pipe, and then impacts the main turbine rotor impeller to work. Along the way, the rotor blades and straight conical surface cylinder shaft guide the condensed heat from the center of the compressor into the inner volute return chamber, which is immediately sucked into the compressor. The compressed refrigerant flows to the turbine through the straight conical surface cylinder and the impeller fixed thereon, and then flows to the heat exchanger pipe of the heat exchange chamber, and the high-pressure refrigerant is liquefied by heat dissipation, and then impacts the small turbine in the hub of the high-speed rotating compressor, and the outlet is the collecting chamber. Thus, the cycle is continuously repeated, and after stable operation, the starting motor power supply can be disconnected, and the external source can be continuously driven by the main shaft output power to drive the propeller and / or the generator. In addition to the need for regular maintenance due to mechanical wear, it can continue to operate.

[0089] If the machine needs to be stopped, the output line of the electric motor is disconnected, and the liquid refrigerant in the collecting chamber is quickly extracted to the storage tank. Since the amount of refrigerant in the machine is too small to sustain the cycle, the machine automatically stops.

[0090] The generator set of the present application can also be placed high above the city to eliminate the heat island effect, and can also be used to create a local cool atmosphere for large-scale celebration activities. The present application can even be used as a tool for artificial intervention in weather, which can generate electricity and cause precipitation in areas with long-term drought and little rain. The present application can also be used as a tool for fresh water production, and can also produce sea ice while generating electricity. The generator of the present application can also be installed on a train to provide power for it, without the need to pull an electric network along the way.

[0091] The above describes the present application and its embodiments, which are not limited, and the actual protection scope is not limited thereto. Any changes or replacements within the technical scope disclosed by the present application can be easily thought of by those skilled in the art, which should be covered within the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the protection scope of the claims.

Claims

1. A heat pump engine, characterized by, Multi-stage impeller compressor is surrounded by multi-stage impeller turbine, the straight conical cylindrical shell of compressor is the rotor and power output cylinder of turbine, turbine outlet centripetal turn back, which is the compressor inlet, conducive to the recovery of compression heat, also conducive to the compact and reasonable layout of the overall structure; Including: Main shaft (35) - with straight conical cylindrical shell slender neck inside and outside spline form connection, main shaft (35) and main shaft front bearing (27) with thread connection; High pressure dynamic sealing ring (28) behind main shaft front bearing (27) blocks high pressure liquid flow of liquid collecting ring chamber (29); Head cone fairing (1), head cone fairing (1) and inlet guard (24) and outer ring are fixed as a whole, cover the front end of two half barrel shaped shroud and fixed with screw, shroud is fastened with edge strip (20) by bolt; Front propeller (2), rear propeller (21) - blade and hub are an integral whole, bolted to the head and tail of main shaft (35); Front generator (3, 26), gas collecting chamber (30), front generator (3, 26) and gas collecting chamber (30) are separated by front cabin partition base, Front support (5) between shroud and main body is fused together with the outer side of the front end of the front segment of the main body shell, each support is arranged radially in axial view and consistent with the direction and number of evaporation pipes (6) extending radially on the outer wall of gas collecting chamber (30); The outer periphery of each support is fused with a rim that can fit the corresponding part of the shroud, and is screwed to the inner side of the shroud; The front and rear edges of each support are blade edges, thick in the middle, and the rear edge is fixed with a rib in front of the evaporation pipe (6) by bolt and nut; Each evaporation pipe (6) is longitudinally placed and arranged radially, and is loose at the front and rear ends before assembly. The front end is curved centripetally and integrated with a nearly circular truncated ring cylinder that closely fits the outer wall of the front segment of the main body shell, and is screwed to the outer wall of the front segment of the main body shell. The tail end of each evaporation pipe (6) is fastened by a nut on the tail seat (44) with external threads; The main body shell surrounded by each evaporation pipe (6) is divided into two segments; The inner side of the front end of the front segment is screwed to the front cabin partition base; The rear end and the front end of the rear segment are screwed to the hollow outer shell of the compressor stator (9); The inner side of the rear end of the rear segment is screwed to the rear cabin partition base; Liquid flow core pipe (7) - the liquid flow core pipe (7) of each evaporation pipe extends from the front end of the evaporation pipe, passes through the gas collecting chamber (30), and rotates into the inner wall of the ring chamber (30) through the middle screw; The liquid flow hole is connected with the liquid collecting ring chamber (29) at the outlet of the small turbine (32), and a proper amount of radial tripod support is fixed on each liquid flow core pipe (7) to keep the liquid flow core pipe (7) centered in the evaporation pipe (6); The end of each liquid flow core pipe (7) is fastened to the control valve in the rear support (44) by a middle screw against the pipe end flange; The front and rear edges of each support are blade edges, thick in the middle, and the rear support is opened at the same side middle and rear position and covered with screws, because the hollow support has a row of tail seats and control valves of each evaporation pipe (6), which is convenient for assembly and maintenance; Heat exchange chamber radiator (12) - base is fixed to the outside of straight conical cylindrical shell neck with spline form, and is fixed to the stator of small turbine (32) with spline form, which is fixed to the outside of straight conical cylindrical shell slender neck. The base has supports for the radiator (12) at the inlet and outlet ends of the heat exchange chamber and is integrated with the base; The radiator (12) is screwed into the base at the outlet end of the heat exchange chamber with a middle bolt against the pipe end flange to communicate with the orifice of the compressor outlet (34) and at the inlet end of the heat exchange chamber in the same way to communicate with the orifice of the turbine inlet (32); The compressor rotor (8) is constrained to the base of the radiator (12) at the rear end with a high pressure dynamic seal ring (33) with sliding bearing and at the front end with a high pressure dynamic seal ring (31) with sliding bearing inside the inner wall of the collector ring chamber (30); The stern nozzle (23) with jet flow guide groove is integrated with the outlet grille (45) and the stern cone whole cover (46), the front end of which covers the rear end of the two half barrel-shaped shrouds and is fastened with screws; The compressor inner rotor (37) is connected with the inside of the straight-line conical cylinder throat part at the front end of the cylinder shaft with a high pressure dynamic seal ring (10) and is connected with the main shaft (35) at the rear end with a conical roller bearing, the outer end of which is fixed with the sun gear (40) of the planetary gear and the inner end of which supports the large end bearing (15) of the straight-line conical cylinder; The ring gear (41) of the planetary gear is fixed with spline form to the rear section of the main shaft (35) with the wheel hub of the disc wheel, the front end of the rear section of which is fixed with internal thread to the ring gear (41), the rear of which has the outer sleeve shaft end head bearing (16) of the main shaft (35) and is pressed against the main shaft (35); The centripetal inner volute backflow chamber (38) is separated from the chamber of the rear starting and power generation integrated machine (42, 43) by the rear cabin separation base, the front end of the front section of which is fixed with the front end of the main shaft front bearing (27), then the front power generator (3, 26) is installed, and then the front end cover is installed, which is fixed with screws on the front cabin separation base, the paddle shaft seal ring (25) is installed on the front end cover, the seal ring cover is fixed with screws on the front end cover, and the front propeller is fastened to the front end of the main shaft with a washer nut; The rear cabin separation base is fixed with the rear section of the main body shell, the rear end of which is fixed with the planetary gear (18, 40) with screws, the ring gear hub is fixed with spline form to the main shaft (35), the rear starting and power generation integrated machine (42, 43) is installed, the seat of the starting and power generation integrated machine (43) is fixed with screws on the rear cabin separation base, the seat of the stator (43) is also the seat of the main shaft rear bearing (19), the inner ring of the bearing (19) is constrained to the main shaft (35) by the stop washer, the stop washer fixed with thread to the main shaft constrains the bearing (19) and the ring gear hub (41), the rear end cover with paddle shaft seal ring (22) is fixed with screws on the rear cabin separation base, the seal ring cover is fixed with screws on the rear end cover, and the rear propeller (21) is fastened to the rear end of the main shaft (35) through a washer nut; The outer sleeve shaft end head of the main shaft and the rear cabin separation base are provided with a seal ring (39) to separate the centripetal inner volute backflow chamber (38), the planetary gear (18, 40) chamber, and the starting and power generation integrated machine (42, 43) chamber. The rear support (44) is fused with the rear cabin base periphery and is radially distributed, and is consistent with the longitudinally placed radial evaporation pipe (6); the periphery is also fused with a wheel rim that can be attached to the corresponding part of the shroud, and is fixed to the inside of the shroud with screws; All the blades of the impeller and the hub or the rim (9, 13, 14, 36, 37) are integrally machined, and the hub or the rim is fixedly connected with the corresponding part in the form of a spline.

2. A heat pump engine according to claim 1, further characterized by There must be a multi-stage impeller type compressor between the gas collection chamber and the turbine, and there must be a heat exchange chamber between the compressor and the turbine. The high-pressure and high-temperature refrigerant must pass through the heat sink to release the latent heat of condensation into liquid state. The main shaft in the straight-line conical cylinder must have a reverse sleeve shaft, and the multi-stage impeller fixedly connected outside the sleeve shaft and the multi-stage impeller fixedly connected inside the conical cylinder are alternately arranged and reversed, which greatly improves the compression efficiency. A small turbine driven by the high-pressure liquid flow from the outlet of the heat sink is placed between the compressor hub and the slender neck of the straight-line conical cylinder. The guide vane is fixed to the outside of the slender neck, and the rotor is fixed to the inside of the compressor hub. This not only recovers part of the pressure energy of the high-pressure liquid flow, but also makes the compressor rotor rotate faster than the turbine speed. The power machine includes several temperature, pressure, and speed sensors, as well as an electronic control system that prevents private disassembly and relocation and self-destructs. The self-destructive charge is placed in the front (4) of the cabin base, in the hollow shell of the compressor stator (11), and in the rear (17) of the cabin base.

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