heat pump motor

Abstract

The present invention discloses a heat pump motor that can convert the internal energy of the atmosphere and of the seawater absorbed by the low-boiling-point refrigerant into kinetic energy to drive propellers and generators, thus becoming a completely new power generation plant and a completely new ship propulsion system that consumes no energy fuel and operates stably over a long period; it can thoroughly solve a number of problems such as the conflicts of interest caused by fossil energy, including crust destruction, pollution, high electricity generation costs and unequal global distribution, the severe limitations of photovoltaics, wind power and hydropower caused by weather and environmental location, and the very unstable power supply;After being throttled and decompressed by the control valve, the high-pressure liquid refrigerant enters the evaporation tube to absorb heat from the ambient heat source at a low temperature. It evaporates and expands, and is forced by the compressor into the heat exchange chamber. After absorbing the heat released by the compressor-compressed and heated refrigerant, it heats up further and expands. Upon reaching the turbine to perform work, the refrigerant is drawn into the compressor for compression. It also releases latent heat, condenses back into a liquid state, and enters the small turbine that drives the air compressor. It flows back through the liquid flow core tube to the control valve and circulates continuously, with the turbine driving the compressor, propellers, and generator.

Description

Technical area

[0001] The present invention relates to the technical field of heat pump motors and relates in particular to a heat pump motor that combines heat pump technology and aviation engine technology. Background technology

[0002] The energy necessary for human survival and development is usually in the form of thermal, mechanical, and electromagnetic energy, which can be converted into one another, with electrical energy being the most widely used. To obtain this energy, in addition to the current light energy from the sun and converted wind energy, the mechanical energy of water, the chemical energy of plants, etc., which can be converted into electricity using solar panels, wind turbines, and turbine-driven generators, there are also fossil energy sources from the Earth's crust, such as gasoline, paraffin, diesel fuel, heavy oil, and liquefied petroleum gas, etc., which are derived from petroleum. As in Fig. As shown in Figure 3, chemical energy can be converted into heat, and then into mechanical energy or electricity, using gasoline engines, gas turbines, diesel engines, and turbine-driven boilers. Coal and nuclear fuels, on the other hand, provide thermal energy for thermal and nuclear power plants, which is then converted into electrical energy. Each of these energy sources has its own advantages, but usually also its own difficulties and disadvantages, such as the need for more equipment, the complexity of the production process, low conversion efficiency, pollution, climate change, and, above all, excessively high costs.

[0003] The present invention provides a heat engine with a single heat source in the thermodynamic sense - a heat pump engine that can convert the internal energy of the atmosphere and seawater into kinetic energy to drive propellers and generators, and can end the history of fossil energy. Contents of the invention

[0004] The object of the present invention is to provide a heat pump motor to solve the problems raised by the aforementioned prior art.

[0005] To solve the aforementioned technical problems, the present invention provides the following technical solutions: The heat pump motor of the present invention, wherein a multi-stage impeller compressor is surrounded by a multi-stage impeller turbine, the straight, conical cylindrical housing of the compressor simultaneously serves as the rotor and the cylinder shaft for power output of the turbine, and the centripetal return of the turbine outlet constitutes the compressor inlet, which has a positive effect on the recovery of compression heat and also contributes to the overall compact structure and reasonable layout, comprises the following: Main shaft connected to the narrow neck of the straight conical cylinder by means of internal and external splines, wherein the main shaft is connected to the main shaft front bearing by threads; wherein a dynamic high-pressure sealing ring is located behind the main shaft front bearing, blocking the high-pressure fluid flow in the collecting ring chamber; Nose cone fairing, wherein the nose cone fairing, the inlet grille and the outer ring form a solid whole, covering the front ends of the two semi-cylindrical barrel-shaped protective fairings and fixing them with screws, and the protective fairings being attached to side strips with bolts; Front propeller, rear propeller, wherein the blades and the propeller hub are a single unit and are connected to the head and tail of the main shaft by bolts; Front generator and air collection chamber, separated by the front cabin partition base, the front bracket being rigidly connected between the protective fairing and the main body being integrated with the outer surface of the front end of the front segment of the main body shell, the axial viewing angle of each bracket being radially arranged and corresponding to the direction and number of evaporation tubes extending radially from the outer wall of the air collection chamber; the outer circumference of each bracket being fused with a rim that fits into the corresponding part of the protective fairing and being fastened with screws on the inside of the shield; the front and rear edges of each bracket being blade-shaped and thick in the middle, and screws and nuts being used at the rear edge to fasten the ribs projecting from the front of the evaporation tube; wherein each evaporation tube is arranged vertically and radially, the front and rear ends being loose prior to assembly, and the front end being bent centripetally and integrated with an approximately frustoconical annular cylinder that fits snugly against the outer wall of the front segment of the main body shell and is fastened to the outer wall of the front segment of the main body shell with bolts; the rear end of each evaporation tube being tightened by the externally threaded nut on the tailstock; the main body shell surrounded by each evaporation tube being divided into two sections; the front cabin partition base being bolted to the inside of the front end of the front segment; the rear end and the front end of the rear segment both being bolted to the hollow shell of the air compressor stator; the rear cabin partition base being bolted to the inside of the rear end of the rear segment; Liquid flow core tube, wherein the liquid flow core tube of each evaporator tube extends from the front end of the respective evaporator tube through the air collection chamber and is screwed into the corresponding liquid flow hole in the inner wall of the annular chamber by means of a central screw; the liquid flow holes are all connected to the liquid collection annular chamber at the outlet of the small turbine, and a corresponding number of radial support legs are attached to each liquid flow core tube, such that the end of each liquid flow core tube is secured by means of a central screw in the rear bracket on the tube end flange at the control valve; wherein the front and rear edges of each bracket are blade-shaped and the middle is thick, and the rear brackets are all covered with openings in the middle and rear part of the same side and are fastened with screws, as each hollow bracket has a series of tailstocks and control valves for each evaporation tube, which facilitates assembly and maintenance; Heat exchange chamber cooler, wherein the base is firmly connected to the outside of the neck of the straight conical cylinder in the form of splined teeth and is resisted by the stator of the small turbine, which is also firmly connected to the outside of the slender neck of the straight conical cylinder in the form of splined teeth; The base contains brackets that support and securely connect the cooler at the inlet and outlet of the heat exchange chamber and are integrated into the base; the cooler at the outlet end of the heat exchange chamber is screwed into the opening in the base that is connected to the compressor outlet by pressing the central screw against the flange of the pipe end; at the inlet end of the heat exchange chamber, it is screwed into the opening that is connected to the inlet of the small turbine in the same way; Air compressor rotor, wherein its hub, the rear end, is attached to the base of the cooler by a dynamic high-pressure sealing ring with a sliding bearing; the front end is further restricted by a dynamic high-pressure sealing ring with a sliding bearing in the inner wall of the air collecting chamber; wherein the rear nozzle with the jet redirection groove is integrated into the outlet grille and the rear cone cover, the front end covers the rear ends of the two semi-circular, barrel-shaped protective covers and is fastened with screws; Inner rotor of the compressor, wherein the front end of its cylinder shaft is slidably connected to the inside of the neck of the straight conical cylinder via a dynamic high-pressure sealing ring; the rear end is connected to the main shaft via a tapered roller bearing, the sun gear of the planetary gear is attached to the outside of the end, and the end bearing of the straight conical cylinder with a large opening is supported inside the end; The ring gear of the planetary gear, wherein it is rigidly connected to the rear segment of the main shaft by a disc hub in the form of splined teeth; wherein the front end of the rear machine with integrated starter generator is rigidly connected to the ring gear by means of an internal thread; wherein an outer sleeve shaft end bearing of the main shaft is located in front of the ring gear of the planetary gear, which is mounted on the main shaft and pressed by it; the centripetally inwardly rolled return chamber, wherein the space between it and the rear starter generator is the rear cabin partition base; wherein, after the front cabin partition base is attached to the forward end of the front segment of the main body shell, the main shaft front bearing is installed, and then the front generator is installed, finally the front end cover is installed and bolted to the front cabin partition base; a propeller shaft seal is installed on the front end cover and a sealing ring cover is bolted to the front end cover; the front propeller is attached to the front end of the main shaft with a washer nut; What separates the centripetally inwardly rolled return chamber and the chamber of the rear machine with integrated starter generator is the rear cabin separating base; wherein, after the front cabin separating base is attached to the rear end of the rear segment of the main body shell, the planetary gear is installed, the planetary gear is firmly connected to the rear cabin separating base with bolts, and the hub of the ring gear is firmly connected to the main shaft in the form of splined connections, wherein the rear machine with integrated starter generator is installed, and the seat of the machine with integrated starter generator is firmly connected to the rear cabin separating base with bolts, wherein the seat of the stator is also the seat of the main shaft rear bearing, and the inner ring of the bearing is restricted on the main shaft by a non-return ring;wherein the anti-reverse ring screwed to the main shaft restricts not only the bearing but also the hub of the gear ring; wherein the rear end cover with the propeller shaft seal is firmly connected to the rear cabin partition base with screws, and the seal cover is firmly connected to the rear end cover with screws; wherein the rear propeller is attached to the rear end of the main shaft with the washer nut; wherein a sealing ring is provided between the outer sleeve shaft end of the main shaft and the rear cabin partition base to block the centripetally rolled inwards return chamber, the chamber of the planetary gear and the chamber of the machine with integrated starter generator; wherein the rear support is integrated with the outer circumference of the rear cabin partition base and is evenly radially distributed and corresponds to the longitudinally and radially arranged evaporation tubes; wherein the outer circumference is also integrated with a rim that fits into the corresponding part of the protective clothing and is also fastened with screws to the inside of the protective clothing; wherein the blades of all wheels and the hub or rim are machined in one piece and the inside of the hub or the outside of the rim are firmly connected to the corresponding parts in the form of splined connections.

[0006] As an improvement, the power unit has a series of temperature, pressure and speed sensors, as well as electronic control that prevents unauthorized disassembly, switching and self-destruction, and the self-destructive charge is located at the front of the cabin partition base, in the middle of the hollow shell of the air compressor stator and at the rear of the cabin partition base.

[0007] The present invention incorporates the following key measures: A multi-stage impeller compressor is surrounded by a multi-stage impeller turbine, and the straight, conical cylindrical housing of the compressor is simultaneously the rotor and the cylinder shaft for the power output of the turbine, which has a positive effect on the recovery of compression heat. II. Between the air collection chamber, which gathers the air flowing in from each evaporation tube, and the turbine, there is a multi-stage impeller air compressor that blocks the support of the gaseous refrigerant before the turbine outlet, which, after the recovery of the heat of condensation, is heated and pressurized, so that the evaporation tube outside the control valve is in a state of low pressure and low temperature, in which it evaporates easily and quickly absorbs heat. III. A heat exchange chamber is arranged between the air compressor and the turbine. The high-pressure, high-temperature refrigerant at the outlet of the straight, conical cylinder neck of the compressor condenses back into a liquid state after releasing latent heat via the cooler in the heat exchange chamber. IV. The straight, conical cylinder serves not only as the turbine's power output shaft but also as the compressor housing rotor with integrated multi-stage impellers. A cylindrical shaft rotor is mounted on the outer casing of the main shaft, and the multi-stage impellers attached to it and the multi-stage impellers on the housing rotor are arranged alternately and rotate in opposite directions, significantly improving compression efficiency. V. A small turbine, driven by the high-pressure fluid flow from the radiator outlet, is positioned between the air compressor hub and the narrow neck of the straight, conical cylinder. The stator is rigidly connected to the outside of the extended neck, and the rotor is rigidly connected to the air compressor hub. The small turbine not only recovers some of the pressure energy from the high-pressure refrigerant being forced back into a liquid state, but also ensures that the air compressor rotates faster and more efficiently based on the turbine speed.

[0008] The present heat pump engine differs from existing power machines such as internal combustion engines, external combustion engines, and steam turbines. It consumes no fuel and requires only water from rivers, lakes, and seas, or the not-too-low temperature of the atmosphere, as a heat source. It can convert most of the internal energy absorbed by low-boiling-point refrigerants from rivers, lakes, seas, or the atmosphere into mechanical energy to drive propellers and generators, and no "waste heat" is released to low-temperature heat sources, thus creating a brand-new generator set or marine propulsion engine.

[0009] Compared to combustion engines, which deliver mechanical energy, electric motors deliver mechanical energy, which is cleaner and more convenient. Compared to electricity generation through photovoltaics, wind power, and hydropower, the present invention is much less affected by climate, environment, and geographical location, offers a much more stable power supply, high efficiency, and low costs. Compared to coal-fired boilers, oil (gas) boilers, and nuclear reactor boilers plus steam turbine generator units, the present invention features a compact and sophisticated structure, a small footprint, simple installation, consumes no fuel, and provides inexpensive, readily available fuel and simple electrical energy.Compared to nuclear power in ships, the propulsion unit of the present invention has a compact and lightweight structure, occupies no cabin space, poses no risk of nuclear contamination, and has low operating costs. Compared to the diesel engine and gas turbine power of surface vessels, the structure of the present invention is compact and lightweight and can be raised below the waterline at the stern of the ship. It not only takes up no cabin space, but also eliminates the need to carry fuel, significantly reduces electricity costs, and has a lifespan comparable to that of nuclear power. Compared to diesel-electric propulsion in submarines, the advantages and disadvantages of the propulsion system according to the invention are even more pronounced. It can also be used as an energy source for helium-powered boats in airspace where atmospheric temperatures are not too low.Compared to photovoltaic power generation, batteries, motor power, and gasoline engine power, the present invention is more stable and durable. When flying exclusively in low-altitude airspace, its endurance is comparable to nuclear power, and it is cheaper and much safer. Figures

[0010] To more clearly explain the embodiments of the present invention or the prior art technical solutions, the drawings necessary for describing these embodiments or the prior art are briefly presented below. Obviously, the drawings listed below are only some schematic structural diagrams of the present invention, but not all of them. Fig. Figure 1 is a schematic structure diagram of the heat pump motor of the present invention. Fig. Figure 2 is a diagram of an embodiment of the heat pump motor of the present invention. Fig. Figure 3 is a technical background diagram of the heat pump motor of the present invention. Reference symbols in the figures:

[0011] Nose cone fairing 1; Front propeller 2; Front generator 3; Front cabin partition base 4; Front bracket 5; Evaporator tube 6; Liquid flow core tube 7; Air compressor rotor 8; Air compressor stator 9; Dynamic high-pressure sealing ring 10; Air compressor stator hollow shell 11; Radiator 12; Turbine stator 13; Turbine rotor 14; End bearing of straight conical cylinder with large opening 15; Outer sleeve end bearing of main shaft 16; Rear cabin partition base 17; Planetary gear carrier 18; Main shaft rear bearing 19; Side strip 20; Rear propeller 21; Propeller shaft seal 22; Rear nozzle 23; Inlet grille 24; Propeller shaft seal 25; Front generator 26; Main shaft front bearing 27; Dynamic high-pressure sealing ring 28; Collector chamber 29; Air collection chamber 30; dynamic high-pressure sealing ring 31; small turbine 32; dynamic high-pressure sealing ring 33; compressor outlet 34; main shaft 35; compressor outer rotor 36; compressor inner rotor 37; centripetally rolled return chamber 38;Sealing ring 39; sun gear 40; ring gear 41; machine with integrated starter generator 42; machine with integrated starter generator 43; rear bracket 44; exhaust grille 45; rear cone fairing 46; Specific embodiments

[0012] The present embodiment describes a heat pump motor in detail with reference to the Fig. 1 to 2.

[0013] Heat pump motor of the present embodiment, wherein a main shaft 35 is connected to the narrow neck of the straight conical cylinder by means of internal and external splines, wherein the main shaft 35 is connected to the main shaft front bearing 27 by threads; wherein a dynamic high-pressure sealing ring 28 is located behind the main shaft front bearing 27, which blocks the high-pressure fluid flow in the collecting ring chamber (29); The main shaft is a stepped shaft in the middle and front area (where the external splines are connected to the internal splines of the narrow neck of the straight conical cylinder), which is thick and tapered at both ends; The nose cone fairing 1, the inlet grille 24 and the outer ring form a solid whole; they cover the front ends of the two semi-cylindrical barrel-shaped protective fairings and fix them with screws, and the protective fairings are attached to side strips 20 with bolts; Front propeller 2, rear propeller 21, wherein the blades and the propeller hub form a single unit and are connected to the head and tail of the main shaft 35 by bolts; The front generator 3, 26 and the air collection chamber 30 are separated by the front cabin partition base, The front bracket 5, which is firmly connected between the protective cover and the main body, is integrated with the outer surface of the front end of the front segment of the main body shell; the axial viewing angle of each bracket is radially arranged and corresponds to the direction and number of the evaporation tubes 6, which extend radially from the outer wall of the air collection chamber 30; the outer circumference of each bracket is fused with a rim that fits into the corresponding part of the protective cover and is fastened with screws on the inside of the shield; the front and rear edges of each bracket are blade-shaped and thick in the middle, and screws and nuts are used at the rear edge to fasten the ribs projecting from the front of the evaporation tube 6; Each evaporation tube 6 is arranged vertically and radially; prior to assembly, the front and rear ends are loose, and the front ends are all bent centripetally and integrated with an approximately frustoconical annular cylinder that fits tightly against the outer wall of the front segment of the main body shell and is fastened to the outer wall of the front segment of the main body shell with screws; the rear end of each evaporation tube 6 is tightened by the externally threaded nut on the tailstock 44; the main body shell surrounded by each evaporation tube 6 is divided into two sections; the front cabin partition base is fastened with screws to the inside of the front end of the front segment; the rear end and the front end of the rear segment are both fastened with screws to the hollow shell of the air compressor stator 9; the rear cabin partition base is fastened with screws to the inside of the rear end of the rear segment; Liquid flow core tube 7, wherein the liquid flow core tube 7 of each evaporator tube extends from the front end of the respective evaporator tube through the air collection chamber 30 and is screwed into the corresponding liquid flow hole in the inner wall of the annular chamber 30 with a central screw; wherein the liquid flow holes are all connected to the liquid collection annular chamber 29 at the outlet of the small turbine 32 and a corresponding number of radial support legs are attached to each liquid flow core tube 7 to always position each liquid flow core tube (7) centrally in the evaporator tube (6), so that the end of each liquid flow core tube 7 is fastened with a central screw in the rear bracket 44 on the tube end flange at the control valve; The front and rear edges of each bracket are blade-shaped and the middle is thick, and the rear brackets are all covered with openings in the middle and rear part of the same side and fastened with screws, as each hollow bracket has a series of tailstocks and control valves for each evaporation tube 6, which facilitates assembly and maintenance; Heat exchange chamber cooler 12, wherein the base is firmly connected to the outside of the neck of the straight conical cylinder in the form of splined connections and is resisted by the stator of the small turbine 32, which is also firmly connected to the outside of the slender neck of the straight conical cylinder in the form of splined connections; on the base are brackets that support and firmly connect the cooler 12 at the inlet and outlet of the heat exchange chamber and are integrated into the base; wherein the cooler 12 is screwed into the opening in the base at the outlet end of the heat exchange chamber, which is connected to the compressor outlet 34, by pressing the central screw against the flange of the pipe end; it is screwed into the opening at the inlet end of the heat exchange chamber in the same way, which is connected to the inlet of the small turbine 32; Air compressor rotor 8, wherein its hub, the rear end, is attached to the base of the cooler 12 by a dynamic high-pressure sealing ring 33 with a sliding bearing; wherein the front end is further restricted by a dynamic high-pressure sealing ring 31 with a sliding bearing in the inner wall of the air collecting chamber 30; The rear nozzle 23 is integrated with the jet diversion groove into the outlet grille 45 and the rear cone cover 46; the front end covers the rear ends of the two semicircular, barrel-shaped protective covers and is fastened with screws; Inner rotor of the compressor 37, wherein the front end of its cylinder shaft is slidably connected to the inside of the neck of the straight conical cylinder via a dynamic high-pressure sealing ring 10; the rear end is connected to the main shaft 35 via a tapered roller bearing, the sun gear 40 of the planetary gear is attached to the outside of the end, and the end bearing 15 of the straight conical cylinder with large opening is supported inside the end; The ring gear of the planetary gear 41, wherein it is firmly connected to the rear segment of the main shaft 35 by means of a disc hub in the form of splined teeth; wherein the front end of the rear machine with integrated starter generator 42 is firmly connected to the planetary gear ring 41 by means of an internal thread; wherein an outer sleeve shaft end bearing 16 of the main shaft is located in front of the ring gear of the planetary gear ring 41, which is mounted on the main shaft 35 and pressed by it; wherein the space between the centripetally rolled inwards return chamber 38 and the chamber of the rear machine with integrated starter generator 42, 43 is the rear cabin partition base; wherein, after the front cabin partition base is attached to the forward end of the front segment of the main body shell, the main shaft front bearing 27 is installed, and then the front generator 3, 26 is installed, finally the front end cover is installed and fastened to the front cabin partition base with screws; a propeller shaft seal 25 is installed on the front end cover and a sealing ring cover is fastened to the front end cover with screws; wherein the front propeller is fastened to the front end of the main shaft with a washer nut; After the front cabin partition base is attached to the rear end of the rear segment of the main body shell, the planetary gear 18, 40 is installed, the planetary gear 18 is firmly connected to the rear cabin partition base with screws, and the hub of the ring gear is firmly connected to the main shaft 35 in the form of splined connections, the rear machine with integrated starter generator 42, 43 is installed, and the seat of the machine with integrated starter generator 43 is firmly connected to the rear cabin partition base with screws, the seat of the stator 43 also being the seat of the main shaft rear bearing 19, and the inner ring of the bearing 19 is restricted by a non-return ring on the main shaft 35; the non-return ring screwed to the main shaft restricts not only the bearing 19, but also the hub of the ring gear 41;The rear end cover with the propeller shaft seal 22 is firmly connected to the rear cabin partition base with screws, and the sealing ring cover with screws is firmly connected to the rear end cover; the rear propeller 21 is attached to the rear end of the main shaft 35 with the washer nut; A sealing ring 39 is provided between the outer sleeve shaft end of the main shaft and the rear cabin partition base to block the centripetally rolled inwards return chamber 38, the chamber of the planetary gear 18, 40 and the chamber of the machine with integrated starter generator 42, 43; The rear support 44 is integrated with the outer circumference of the rear cabin partition base and is evenly distributed radially and corresponds to the longitudinally and radially arranged evaporation tubes 6; the outer circumference is also integrated with a rim that fits into the corresponding part of the protective clothing and is also fastened to the inside of the protective clothing with screws; The blades of all wheels and the hub or rim 9, 13, 14, 36, 37 are manufactured in one piece and the inside of the hub or the outside of the rim are firmly connected to the corresponding parts in the form of splined connections.

[0014] The power unit has a series of temperature, pressure and speed sensors as well as an electronic control system that prevents unauthorized disassembly, switching and self-destruction, and the self-destructive charge is located at the front in the cabin partition base 4, in the middle of the hollow shell of the air compressor stator and at the rear in the cabin partition base 17.

[0015] In this specific design, the properties of the low-boiling-point refrigerant, that it absorbs heat, evaporates, expands and performs work under low pressure and low temperature, and the properties of the heat dissipation condensate, that it absorbs heat again, evaporates, expands and performs work when carried out at high temperature and high pressure, can be used.It is sealed in the closed circulating flow channel of “evaporator - air collection chamber - air compressor - heat exchange chamber - turbine - centripetal return chamber - compressor - cooler in the heat exchange chamber - high-pressure liquid flow turbine driving the air compressor - liquid collection chamber connected to the liquid storage - liquid flow core tube in the middle of each evaporation tube - control valve at the end of the core tube - evaporator”, and the evaporator is immersed in the water of rivers, lakes and seas or the atmosphere with a temperature of not less than 0 °C.

[0016] The compressor compresses the gaseous refrigerant into a liquid state at ambient temperature and low pressure. After cooling through the condenser in the center of the heat exchange chamber, it encounters the small turbine that drives the air compressor, releasing some of its pressure energy into the liquid collection chamber. It then flows into each liquid core tube of the evaporator, located in the four walls, and enters the evaporation tube after being throttled and depressurized by the control valve. There, it absorbs heat energy from the external ambient heat source introduced into the tube wall and evaporates, expanding and gaining pressure. It then flows into the collection chamber and is forced by the air compressor into the condenser of the heat exchange chamber.It is further heated by the heat released from the condensed refrigerant, pressurized, expands and then hits the (main) turbine rotor wheel, and upon impact it absorbs the heat released by the compressor, which is introduced via the blades and the rotating shaft, thus generating more kinetic rotational energy.

[0017] The turbine's rotation drives the compressor and the main shaft, which in turn drives the propeller and generator. Simultaneously, the alternately configured compressor, driven via planetary gears, rotates the impeller at twice the speed to improve its compression efficiency. Most of the mechanical energy consumed by the compressor is recovered as condensation heat, with a small portion using pressure energy to impart to the small turbine, which sets the air compressor into high rotational speed. Meanwhile, a low-pressure area is created at the main turbine's outlet, giving the main turbine greater kinetic rotational energy.

[0018] Take as an example a ship propulsion unit with 50 MW / unit: as in Fig. 2 shown.

[0019] In order for the refrigerant to continuously absorb heat, evaporate, and expand, then recover the heat from compression, condensation, and release, expand further and be pressurized to perform work, and then be compressed back into a liquid state, release heat, and then flow back to the evaporator, without stopping and thus continuously delivering power, the refrigerant should be enclosed in a closed flow path. The power unit must be a multi-stage impeller turbine. The compressor and air compressor must also be of the multi-stage impeller type, and the compressor must be positioned in the center of the turbine and completely enclosed within it. The straight conical cylinder serves as both the inner casing and conical shaft of the turbine and the conical casing of the compressor to allow for the recovery of condensation heat. This is the first key point.

[0020] The turbine casing is a columnar cylinder forming the central segment of the main body shell. The forward and aft extensions transition into the nearly frustoconical front and rear shells, forming, together with the front and rear conical fairings, a spindle-shaped, streamlined body. Each evaporator tube of the evaporator, which absorbs the internal energy of the ambient heat source, is distributed around the circumference of the main body and surrounded by a protective, hip-shaped casing, with the inlet and outlet fitted with protective grilles. The ambient heat source is drawn in by the front propeller through the inlet grille and flows across the surface of each evaporator tube, where it is absorbed and cooled. As it is compressed and accelerated through the gradually narrowing flow channel, it is driven by the rear propeller and ejected through the outlet guide vane.

[0021] The multi-stage impeller of the turbine rotor is rigidly connected to the outer wall of the straight conical cylinder within the main body and is arranged alternately with the stator guide impeller, which is attached to the inner wall of the main body shell. The axis of the straight conical cylinder is equipped with a main shaft that runs through the front and rear and is rigidly connected to the neck of the conical cylinder by a column-shaped cylinder with a conical tip.

[0022] The multi-stage impeller of the compressor is mounted on the inner wall of the conical cylinder and alternates with the multi-stage impeller of the counter-rotating compressor, which is mounted on the outer wall of the main shaft's outer sleeve. The inner and outer surfaces of the cone's bell-shaped opening are the compressor inlet and turbine outlet, respectively. At the point where the outlet transitions to the inlet, there is a recirculation chamber, angled 180 degrees inwards, through which the gaseous refrigerant flows out of the turbine and is drawn into the compressor. This chamber is also known as the inwardly rolled return chamber.

[0023] A gap exists between the neck of the conical tip of the straight conical cylinder and the main shaft before the columnar cylinder is firmly held to the main shaft. The annular groove is the compressor outlet and is firmly connected via the numerous holes arranged around the columnar cylinder to the radially distributed heat pipes of the radiator, with the other end of each heat pipe opening into the inlet of the small turbine that drives the air compressor.

[0024] The heat exchange chamber with its integrated cooler is axially connected to the air compressor and turbine. This arrangement is the second key element; the air compressor and the heat exchange chamber are essential. The presence of the air compressor allows the gaseous refrigerant entering the heat exchange chamber to then encounter the turbine rotor, fully recover the heat released during condensation, be heated, and pressurized without any shock effect from the upstream refrigerant. This allows the refrigerant to evaporate more smoothly at low pressure downstream of the throttle valve. Simultaneously, the latent heat must be dissipated in the cooler before the refrigerant returns to the evaporator.

[0025] The multi-stage impeller of the air compressor, i.e., the rotor, features dynamic high-pressure sealing rings with bearings at the front and rear ends of the hub. These bearings are mounted on the inner wall of the fluid collection chamber at the front cabin partition base and on the radiator base, respectively. The rotor is driven by a small turbine powered by a high-pressure fluid flow from the radiator. The corresponding, alternately arranged multi-stage guide wheels are rigidly connected to the hollow stator shell on the inner wall of the main body shell via their outer circumferential rims. Based on the speed of the main turbine, the air compressor is accelerated and rotated by the small turbine, which is driven by the high-pressure fluid flow. This significantly improves its compression efficiency and partially restores the fluid flow pressure. This is the third key point.

[0026] Further forward, in the air collection chamber in front of the air compressor inlet, the gaseous refrigerant collects. This refrigerant flows out of the outlets of the individual evaporator tubes, which are evenly distributed around the outer perimeter wall, and absorbs heat from the ambient heat source. Simultaneously, the liquid flow core tube runs through the center of each evaporator tube in the annular air collection chamber and is connected to the annular liquid collection chamber at the outlet of the small turbine in the central inner wall.

[0027] The air intake chamber at the front of the main body not only restricts the main shaft but also separates the front cabin partition from the front generator chamber. The main shaft passes through the sealing ring in the center and is rigidly connected to the anti-retraction pin ring and restricted by the bearing. It then enters the rear generator chamber and is rigidly connected to the generator rotor. It continues forward through the central sealing chamber of the truncated cone-shaped main body shell to be rigidly connected to the front propeller. The propeller hub is shaped like a smaller truncated cone and, together with the conical fairing in the center of the intake grille, forms the front segment of the conical, streamlined body.

[0028] The periphery of the main body shell at the front cabin partition base is rigidly connected to the front bracket, which protects the front end of the evaporator and supports the front part of the protective shell. The rear wall of the inwardly rolled return chamber along the main shaft forms the aft cabin partition base, separating the inwardly rolled return chamber from the aft generator chamber. If the machine's primary function is boat propulsion, the periphery of the main body shell at the aft cabin partition base is also rigidly connected to the rear bracket, which protects the rear end of each evaporator evaporator tube and supports the rear part of the protective shell. If the primary function is solely to generate electricity, the rear bracket forms the rear output grille, and the conical fairing in the center is also part of the main body shell, thus forming the rigidly connected rear cone.At the same time, the rear segment of the protective shell does not need to shrink to compress the overflow heat source and thus accelerate the outflow to achieve a reverse thrust.

[0029] The main shaft and its outer sleeve shaft pass through the rear cabin partition base and are constrained by bearings located within it. After passing through, the sleeve shaft is rigidly connected to the sun gear of the planetary gear set on the planet carrier, which is rigidly connected to the cabin partition base. Once the main shaft has passed the sun gear, it is rigidly connected to the ring gear of the planetary gear set. The alternately arranged compressor impellers are rigidly connected to the outer wall of the sleeve shaft and the inner wall of the straight conical cylinder, rotating at high speed, which can significantly improve compression efficiency. This is the fourth key point.

[0030] The main shaft in the stern generator chamber is rigidly connected to the outer face of the planetary gear ring, extends further aft, and is rigidly connected to the rotor of the machine with integrated generator starter. If the primary function of the single-source heat engine is marine propulsion, the main shaft passes through the sealing chamber in the center of the frustoconical stern of the main hull and is rigidly connected to the stern propeller. The stern segment of the main hull, together with the propeller hub and the fairing in the center of the exhaust manifold, forms the stern segment of the twin-pronged, pike-shaped, and streamlined body. If the primary function of the machine is solely power generation, the stern propeller is omitted. The exhaust grille is the aft support that holds the rear end of the evaporator tube and supports the stern segment of the hull.The cone-shaped fairing is also part of the main body shell, i.e., the tail cone, and the cross-section of the heat source overflow between the main body and the protective shell does not need to be constricted to accelerate the flow without pressure and obtain thrust.

[0031] In summary, the appearance of the single-source heat engine of the present invention closely resembles a turbojet engine without an afterburner. The outer shell is a drum-shaped protective casing with front and rear openings and a protective grille. The inner part is a streamlined main body, approximately cylindrical in the middle and tapering to a conical shape at both ends. It is coaxial with the protective casing and maintains sufficient clearance for the flow of ambient heat sources through the evaporation tubes, which are designed to heat the vertically arranged, low-boiling-point refrigerant. The front ends of all evaporation tubes are bent centripetally, attached to the circumferential annular wall of the air collection chamber, and open, and firmly connected to the front support via ribs.The front end of the refrigerant fluid flow core tube, located on the axis of each evaporation tube, extends deep into the fluid collection chamber at the outlet of the small turbine. This is driven by the high-pressure fluid flow that powers the air compressor, causing it to rotate within the inner wall of the annular air collection chamber. The fluid flow core tube continues rearward along the axis of the evaporation tube to the rear section. The connection is rigidly attached to the control valve, and the rear end of the evaporation tube is rigidly connected to the rear support. The front and rear supports rigidly connect the main body and the protective shell as a whole. The main body, rigidly connected to the front and rear supports, forms the front and rear cabin partition base, thus roughly dividing the main body into three compartments.The main generator is located in the forward cabin. The middle cabin contains an annular air collection chamber and a surrounding annular liquid collection chamber, an air compressor, and a small turbine driven by it. The heat exchange chamber and radiator, the turbine and surrounding compressor, and the turbine outlet are rotated 180 degrees inwards towards the inwardly rolled return chamber of the compressor inlet. The aft cabin houses a machine with an integrated starter generator and a clutch that drives the stern propeller (when the primary function is boat propulsion). The driven splined shaft of the clutch is rigidly connected to the stern propeller, and the drive splined hub is rigidly connected to the rear end of the main shaft.The main shaft is rigidly connected forward to the rotor of the machine with integrated starter generator. The planetary carrier is rigidly connected to the ring gear of the planetary gearbox on the rear cabin partition base. One end of the shaft connects to the sun gear, while the other end terminates on the sleeve shaft at the neck of the straight conical cylinder. This shaft serves both as the conical output shaft of the main turbine and as the narrow neck of the straight conical cylinder of the compressor housing. After passing through the front cabin partition base and being constrained by the bearings within it, the main shaft is rigidly connected to the main generator rotor of the front cabin. It then passes through the forward sealing chamber and is finally rigidly connected to the front propeller.The outer wall of the straight conical cylinder shaft is rigidly connected to the rotating impeller of the multi-stage turbine, which alternates with the static (guide) impeller attached to the inner wall of the main body shell. The multi-stage compressor impellers, attached to the inner wall of the conical cylinder shaft, alternate with the counter-rotating multi-stage impellers attached to the outer wall of the main shaft's outer sleeve. The inlet end of each liquid heat dissipation tube of the cooler in the heat exchange chamber upstream of the turbine inlet is centripetally rigidly connected to the neck of the straight conical cylinder shaft and communicates with the annular outlet groove of the compressor.The outlet communicates with the inlet of the small turbine in the hub, which drives the air compressor. The small turbine is mounted outside the narrow neck of the straight, tapered cylinder of the main shaft. The guide impeller is fixed to the outer wall of the narrow neck, and the alternately arranged movable impellers are fixed to the inner wall of the air compressor hub. The rear end of the air compressor hub is constrained by the one-way bearing and the dynamic high-pressure seal at the radiator base outside the tapered cylinder neck, and the front end is constrained by the bearings and the dynamic high-pressure seal at the outer wall of the fluid collection chamber in the front cabin partition base.The small turbine has a rear inlet to receive the high-pressure jet flow from each heat pipe of the cooler and a front outlet to collect the fluid in the fluid collection chamber. In addition to the fluid flow core tubes on the surrounding outer walls, which are radially connected to the axis of each evaporation tube, the fluid collection chamber also communicates with the fluid storage tank outside the protective shell via the front cabin partition base and the pipes in the front bracket.

[0032] Therefore, when starting the machine, the required power is connected to the starter, and simultaneously, a corresponding quantity of liquid refrigerant is injected from the liquid storage tank into the liquid collection chamber. Driven by the compressor, the liquid refrigerant enters the liquid flow core tube at the axis of each evaporation tube, continuing to the end. After the release is controlled by the end control valve, the liquid refrigerant absorbs heat from the ambient heat source supplied by the evaporation tube wall, evaporates, expands, and flows towards the air collection chamber. It is further pressurized by the air compressor and directed into the heat exchange chamber. There, it absorbs heat from the radiator tube and then strikes the main turbine rotor to perform work.It absorbs the condensation heat from the compressor in the center, which is introduced along its path by the rotor blades and the straight, conical cylindrical drive shaft upon impact, and enters the inwardly rolled return chamber, from where it is rapidly drawn into the compressor. During compression, heat is transferred via the straight, conical cylindrical shaft and the impeller rigidly attached to it to the turbine and flows to the cooling tube of the heat exchange chamber. After the high-pressure refrigerant has carried away the heat and liquefied, it strikes the small turbine in the hub, which sets the air compressor into high rotational speed, and the outlet is the liquid collection chamber. In this continuous cycle, the starter's power supply can be interrupted after stable operation. Power is then continuously delivered via the main shaft to drive the propeller and / or the generator.It can be operated continuously, regardless of mechanical wear and tear and regular maintenance.

[0033] Should a shutdown be necessary, the generator's output line is disconnected and a corresponding amount of liquid refrigerant is quickly drawn from the liquid collection chamber into the liquid storage tank. Since the amount of refrigerant in the machine is too low to maintain circulation, it shuts down automatically.

[0034] The generator unit of the present invention can also be placed high above a city to eliminate the urban heat island effect and can also create a locally cool atmosphere for large celebrations. The present invention can even be used as an instrument for artificial weather intervention to generate electricity and simultaneously induce rainfall in areas with prolonged drought and low precipitation. The present invention can also be used as an aid in freshwater extraction and can generate electricity during sea ice production. The generator of the present invention can also be installed on a train to provide electricity without the need for a power line en route.

Claims

[1] Heat pump motor, characterized by , that a multi-stage impeller compressor is surrounded by a multi-stage impeller turbine, the straight, conical cylindrical housing of the compressor simultaneously serves as the rotor and the cylinder shaft for the turbine's power output, the centripetal return of the turbine outlet constitutes the compressor inlet, which has a positive effect on the recovery of compression heat and also contributes to the overall compact structure and sensible layout; and that it comprises the following: Main shaft (35) connected to the narrow neck of the straight conical cylinder by means of internal and external splines, wherein the main shaft (35) is connected to the main shaft front bearing (27) via threads; wherein a dynamic high-pressure sealing ring (28) is located behind the main shaft front bearing (27) which blocks the high-pressure fluid flow in the collecting ring chamber (29); Nose cone fairing (1), wherein the nose cone fairing (1), the inlet grille (24) and the outer ring form a solid whole, covering the front ends of the two semi-cylindrical barrel-shaped protective fairings and fixing them with screws, and the protective fairings with side strips (20) being fastened with bolts; front propeller (2), rear propeller (21), wherein the blades and the propeller hub form a single unit and are connected to the head and tail of the main shaft (35) by bolts; Front generator (3, 26) and air collection chamber (30), wherein the front generator (3, 26) and the air collection chamber (30) are separated by the front cabin partition base, wherein the front support (5), which is rigidly connected between the protective cladding and the main body, is integrated with the outer surface of the front end of the front segment of the main body shell, the axial viewing angle of each support being radially arranged and corresponding to the direction and number of the evaporation tubes (6) extending radially from the outer wall of the air collection chamber (30); the outer circumference of each support being fused with a rim that fits into the corresponding part of the protective cladding and being fastened with screws on the inside of the shield; the front and rear edges of each support being blade-shaped and thick in the middle, and screws and nuts being used at the rear edge to fasten the ribs projecting from the front of the evaporation tube (6); wherein each evaporation tube (6) is arranged vertically and radially, the front and rear ends are in a loose state prior to assembly, and the front ends are all bent centripetally and integrated with an approximately frustoconical annular cylinder that fits snugly against the outer wall of the front segment of the main body shell and is fastened to the outer wall of the front segment of the main body shell by screws; the rear end of each evaporation tube (6) is tightened by the externally threaded nut on the tailstock (44); the main body shell surrounded by each evaporation tube (6) is divided into two sections; the front cabin partition base is fastened to the inside of the front end of the front segment by screws; the rear end and the front end of the rear segment are both fastened to the hollow shell of the air compressor stator (9) by screws; the rear cabin partition base is fastened to the inside of the rear end of the rear segment by screws; Liquid flow core tube (7), wherein the liquid flow core tube (7) of each evaporator tube extends from the front end of the respective evaporator tube through the air collection chamber (30) and is screwed into the corresponding liquid flow hole in the inner wall of the annular chamber (30) by means of a central screw; wherein the liquid flow holes are all connected to the liquid collection annular chamber (29) at the outlet of the small turbine (32) and a corresponding number of radial support legs are attached to each liquid flow core tube (7) to always position each liquid flow core tube (7) centrally in the evaporator tube (6), so that the end of each liquid flow core tube (7) is fastened by means of a central screw in the rear bracket (44) on the tube end flange at the control valve; wherein the front and rear edges of each bracket are blade-shaped and the middle is thick, and the rear brackets are all covered with openings in the middle and rear part of the same side and are fastened with screws, since each hollow bracket has a series of tailstocks and control valves for each evaporation tube (6), which facilitates assembly and maintenance; heat exchange chamber cooler (12), wherein the base is firmly connected to the outside of the neck of the straight conical cylinder in the form of splined connections and is resisted by the stator of the small turbine (32), which is also firmly connected to the outside of the slender neck of the straight conical cylinder in the form of wedge-shaped teeth; on the base there are brackets, which support and firmly connect the cooler (12) at the inlet and outlet of the heat exchange chamber and are integrated into the base; wherein the cooler (12) at the outlet end of the heat exchange chamber is screwed into the opening in the base which is connected to the compressor outlet (34) by pressing the central screw against the flange of the pipe end; it is screwed into the opening at the inlet end of the heat exchange chamber in the same way, which is connected to the inlet of the small turbine (32); air compressor rotor (8), wherein its hub, the rear end, is attached to the base of the cooler (12) by a dynamic high-pressure sealing ring (33) with a sliding bearing; the front end is further restricted by a dynamic high-pressure sealing ring (31) with a sliding bearing in the inner wall of the air collecting ring chamber (30); wherein the rear nozzle (23) with the jet diversion groove is integrated into the outlet grille (45) and the rear cone cover (46), the front end covers the rear ends of the two semicircular, barrel-shaped protective covers and is fastened with screws; Inner rotor of the compressor (37), wherein the front end of its cylinder shaft is slidably connected to the inside of the neck of the straight conical cylinder via a dynamic high-pressure sealing ring (10); wherein the rear end is connected to the main shaft (35) via a tapered roller bearing, the sun gear (40) of the planetary gear is attached to the outside of the end, and the end bearing (15) of the straight conical cylinder with a large opening is supported inside the end; The ring gear of the planetary gear (41) is rigidly connected to the rear segment of the main shaft (35) by means of a disc hub in the form of splined teeth; the front end of the rear machine with integrated starter generator (42) is rigidly connected to the ring gear (41) by means of an internal thread; an outer sleeve shaft end bearing (16) of the main shaft is located in front of the ring gear of the planetary gear (41), which is mounted on the main shaft (35) and pressed by it; the centripetally inwardly rolled return chamber (38), wherein the space between it and the chamber of the rear machine with integrated starter generator (42, 43) is the rear cabin partition base; wherein, after the front cabin partition base is attached to the forward end of the front segment of the main body shell, the main shaft front bearing (27) is installed, and then the front generator (3, 26) is installed, finally the front end cover is installed and fastened to the front cabin partition base with screws; wherein a propeller shaft seal (25) is installed on the front end cover and a sealing ring cover is fastened to the front end cover with screws; the front propeller is fastened to the front end of the main shaft with a washer nut; wherein, after the front cabin partition base is attached to the rear end of the rear segment of the main body shell, the planetary gear (18, 40) is installed, the planetary gear (18) is firmly connected to the rear cabin partition base with bolts, and the hub of the ring gear is firmly connected to the main shaft (35) in the form of splined connections, wherein the rear machine with integrated starter generator (42, 43) is installed, and the seat of the machine with integrated starter generator (43) is firmly connected to the rear cabin partition base with bolts, wherein the seat of the stator (43) is also the seat of the main shaft rear bearing (19), and the inner ring of the bearing (19) is restricted by a non-return ring on the main shaft (35); wherein the non-return ring bolted to the main shaft restricts not only the bearing (19) but also the hub of the ring gear (41);wherein the rear end cover with the propeller shaft seal (22) is firmly connected to the rear cabin partition base with screws, and the seal cover is firmly connected to the rear end cover with screws; wherein the rear propeller (21) is attached to the rear end of the main shaft (35) with the washer nut; wherein a sealing ring (39) is provided between the outer sleeve shaft end of the main shaft and the rear cabin partition base to block the centripetally rolled inwards return chamber (38), the chamber of the planetary gear (18, 40) and the chamber of the machine with integrated starter generator (42, 43); wherein the rear support (44) is integrated with the outer circumference of the rear cabin partition base and is evenly radially distributed and corresponds to the longitudinally and radially arranged evaporation tubes (6); wherein the outer circumference is also integrated with a rim that fits into the corresponding part of the protective clothing and is also fastened to the inside of the protective clothing with screws; wherein the blades of all wheels and the hub or rim (9, 13, 14, 36, 37) are machined in one piece and the inside of the hub or the outside of the rim are firmly connected to the corresponding parts in the form of splined connections. [2] Heat pump motor according to claim 1, characterized by, that a multi-stage impeller air compressor must be present between the air collection chamber, which collects the air flowing in from each evaporation tube, and the turbine; wherein a heat exchange chamber must be present between the air compressor and the turbine, and the high-pressure and high-temperature refrigerant must release latent heat via the cooler and condense back into the liquid state; wherein the main shaft in the straight conical cylinder must have a counter-rotating sleeve shaft, the multi-stage impeller attached to the outside and the multi-stage impeller attached to the inside of the conical cylindrical casing are arranged alternately and in reverse, which significantly improves the compression efficiency;wherein a small turbine, driven by the high-pressure fluid flow from the cooler outlet, is placed between the compressor hub and the narrow neck of the straight conical cylinder, the guide vanes are attached to the outside of the narrow neck, and the rotor is attached to the compressor hub, thereby not only recovering some of the pressure energy of the high-pressure fluid flow, but also ensuring that the compressor rotor rotates faster based on the turbine speed; wherein the power unit has a series of temperature, pressure and speed sensors as well as an electronic control system which prevents unauthorized disassembly, switching and self-destruction, and the self-destructive charge is located at the front in the cabin partition base (4), in the middle of the hollow shell of the air compressor stator (11) and at the rear in the cabin partition base (17).

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