A heat sink and closed power generation combined operation system and combined operation method

Abstract

A heat sink and closed-loop power generation combined operation system and a combined operation method belong to the field of thermal management and power generation technology. The present invention solves the problem of heat waste in existing liquid metal-based cooling solutions. It includes a fuel tank, a fuel electric pump, a cooler, a high-temperature heat exchanger, a closed-loop power generation device, a liquid metal electromagnetic pump and a wall cooling channel, wherein the fuel electric pump is connected between the fuel tank outlet and the cooler cold side inlet end through a pipeline, the cooler cold side outlet end is connected to the engine injector through a pipeline, the liquid metal electromagnetic pump, the wall cooling channel and the hot side of the high-temperature heat exchanger are connected in sequence through pipelines to form a loop, and the hot side of the cooler and the cold side of the high-temperature heat exchanger are respectively connected to the closed-loop power generation device through pipelines. The closed-loop power generation system converts thermal energy into electrical energy for use on the machine by performing work externally, reducing the amount of heat transferred to the fuel and improving the heat sink of the fuel.

Description

Technical Field

[0001] The present invention relates to a heat sink and closed-type power generation combined operation system and a combined operation method, belonging to the technical field of heat management and power generation. Background Art

[0002] Thermal protection technology is one of the key technologies in the development of hypersonic flight. Hypersonic vehicles are those traveling at speeds exceeding Mach 5. Scramjet engines are ideal propulsion systems for hypersonic flight. Their simple structure, lightweight weight, high specific impulse, high speed, and high thrust-to-weight ratio make them suitable for sustained hypersonic flight within the atmosphere. However, due to their extremely harsh operating environment, typically operating at high Mach numbers, high-speed air stagnation at the walls during flight generates significant aerodynamic heat. Furthermore, the heat generated by supersonic combustion in hypersonic vehicles is sufficient to melt any metal, and the heat generated by onboard electronic components also needs to be promptly dissipated. Therefore, to ensure the safe and long-term operation of the engine, thermal protection technology for hypersonic vehicles is crucial.

[0003] Regenerative cooling technology, a thermal protection technology for scramjet engines, has been widely used. Cooling channels are created in the engine walls, and fuel is used as a coolant. The fuel in the cooling channels provides convection cooling to the engine walls, while also preheating the fuel. However, conventional regenerative cooling technology faces the problem of fuel cracking and coking, which blocks the cooling channels, rendering the cooling system ineffective and potentially causing engine burnout. To address this fuel cracking and coking issue, a liquid metal-based cooling solution has emerged. However, this cooling solution utilizes only a single heat exchanger to exchange heat between the liquid metal and the fuel. When the engine temperature is too high, the use of only one heat exchanger results in poor heat transfer. The fuel, acting as an indirect coolant, absorbs too much heat, reducing the system's total heat sink while also wasting heat. Summary of the Invention

[0004] The present invention aims to solve the problem of heat waste in existing liquid metal-based cooling solutions, and further provides a heat sink and closed power generation combined operation system and a combined operation method.

[0005] The technical solution adopted by the present invention to solve the above technical problems is:

[0006] A heat sink and closed-loop power generation combined operation system includes a fuel tank, a fuel electric pump, a cooler, a high-temperature heat exchanger, a closed-loop power generation device, a liquid metal electromagnetic pump, and a wall cooling channel, wherein the fuel electric pump is connected between the fuel tank outlet and the cooler cold-side inlet end through a pipeline, the cooler cold-side outlet end is connected to the engine injector through a pipeline, the liquid metal electromagnetic pump, the wall cooling channel, and the hot side of the high-temperature heat exchanger are sequentially connected through pipelines to form a loop, and the hot side of the cooler and the cold side of the high-temperature heat exchanger are respectively connected to the closed-loop power generation device through pipelines.

[0007] Furthermore, an electronic component cooling channel and a skin cooling channel are provided between the outlet of the liquid metal electromagnetic pump and the inlet of the engine wall cooling channel via a pipeline connection.

[0008] Furthermore, the closed-cycle power generation device includes a compressor, a turbine and a generator, wherein the hot side outlet end of the cooler is connected to the compressor, the outlet end of the compressor is connected to the cold side inlet of the high-temperature heat exchanger, the cold side outlet of the high-temperature heat exchanger is connected to the turbine inlet, the turbine outlet is connected to the hot side inlet of the cooler, and the turbine, compressor and generator are coaxially arranged.

[0009] Furthermore, the circulating working fluid in the closed-cycle power generation device is helium or carbon dioxide.

[0010] Furthermore, the liquid metal is a sodium-potassium alloy or a gallium-indium alloy.

[0011] A combined operation method using the above system: low-temperature fuel in the fuel tank is transported to the cold side of the cooler by a fuel electric pump, and liquid metal is transported to the cooling channel by a liquid metal electromagnetic pump. After absorbing heat in the cooling channel, the temperature is increased. The heated liquid metal transfers the heat it carries to a closed-cycle power generation device through a high-temperature heat exchanger. The closed-cycle power generation device converts part of the heat into electrical energy, and the remaining heat is transferred to the low-temperature fuel through the cooler. The fuel that has absorbed heat is passed into the combustion chamber for combustion.

[0012] Compared with the prior art, the present invention has the following effects:

[0013] This application uses liquid metal as a coolant instead of fuel, avoiding the risk of hydrocarbon fuel coking blocking cooling channels and achieving the effect of cooling the entire aircraft. The liquid metal system utilizes the excellent heat transfer capacity of liquid metal to achieve the effect of timely heat transfer. The closed-cycle power generation system uses external work to convert thermal energy into electrical energy for use on the aircraft, reducing heat transfer to the fuel and improving fuel heat sink. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0015] Figure 1 This is a system diagram of this application.

[0016] In the figure: 1. Fuel tank; 2. Electric fuel pump; 3. Cooler; 4. High-temperature heat exchanger; 5. Closed-cycle power generation device; 6. Liquid metal electromagnetic pump; 7. Wall cooling channel; 8. Air inlet; 9. Injector; 10. Combustion chamber; 11. Tail nozzle. DETAILED DESCRIPTION

[0017] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. All other embodiments obtained by ordinary technicians in this field based on the embodiments of the present invention are within the scope of protection of the present invention.

[0018] In the description of the present invention, unless otherwise expressly specified or limited, the terms "mounted," "connected," and "connected" should be understood broadly. For example, they may refer to fixed connections, detachable connections, or integral connections; they may refer to direct connections, indirect connections through an intermediary, or internal communication between two components. Those skilled in the art will understand the specific meanings of these terms in the present invention based on the specific circumstances.

[0019] Specific implementation method 1: Combination Figure 1 This embodiment describes a combined heat sink and closed-loop power generation system, comprising a fuel tank 1, an electric fuel pump 2, a cooler 3, a high-temperature heat exchanger 4, a closed-loop power generation device 5, a liquid metal electromagnetic pump 6, and a wall cooling channel 7. The electric fuel pump 2 is connected via a pipeline between the outlet of the fuel tank 1 and the cold-side inlet of the cooler 3. The cold-side outlet of the cooler 3 is connected via a pipeline to the injector 9 of the engine. The liquid metal electromagnetic pump 6, the wall cooling channel 7, and the hot side of the high-temperature heat exchanger 4 are sequentially connected via pipelines to form a loop. The hot side of the cooler 3 and the cold side of the high-temperature heat exchanger 4 are each connected to the closed-loop power generation device 5 via pipelines. The liquid metal electromagnetic pump 6, the wall cooling channel 7, and the hot side of the high-temperature heat exchanger 4 are sequentially connected via pipelines to form a loop, namely, a liquid metal cooling loop.

[0020] The hot side of the cooler 3 and the cold side of the high-temperature heat exchanger 4 are respectively connected to the closed-cycle power generation device 5 through pipelines to form a closed-cycle power generation system.

[0021] Liquid metal refers to the use of a third fluid different from air and fuel as a coolant instead of fuel. The use of liquid metal in this application fully utilizes the excellent heat exchange capacity of liquid metal to promptly conduct away the heat generated on the aircraft and ensure that the aircraft is in a safe working state. Liquid metal has better heat exchange performance than the working fluid of a closed-cycle power generation system, which helps to improve the safety margin of the aircraft operation. This application combines liquid metal with a closed cycle to convert heat into electrical energy, while reducing the heat absorption of the fuel as an indirect coolant, thereby improving the total heat sink of the system.

[0022] The engine comprises an intake duct 8, an injector 9, a combustion chamber 10, and a tail nozzle 11, arranged in this order. The heat-exchanged fuel enters the combustion chamber 10 through the injector 9, mixes with the compressed air passing through the intake duct 8, and is then burned. The fuel then expands through the tail nozzle 11, generating thrust. The specific structure of the engine is conventional and will not be described in detail here.

[0023] The system of the present application can prevent fuel coking from clogging the wall cooling channel 7, thereby achieving a cooling effect for the entire aircraft and providing sufficient electrical energy for the aircraft.

[0024] After being compressed by shock waves through the inlet 8, the air is mixed with fuel in the combustion chamber 10 and combusted to release heat. Since the scramjet engine operates at a high Mach number, the temperature of the combustion chamber 10 is very high. The liquid metal absorbs heat in the wall cooling channel 7 to cool the engine, ensuring that the wall surface of the combustion chamber 10 does not overheat. The liquid metal acts as an intermediate working medium for heat transfer. After absorbing heat and heating up in the cooling channel, it transfers the heat to the working medium of the closed-cycle power generation system through the high-temperature heat exchanger 4. After releasing heat and cooling down, the liquid metal circulates through the liquid metal electromagnetic pump 6 into the wall cooling channel 7 to continue absorbing heat, forming a closed-loop flow path for the liquid metal.

[0025] The high-temperature liquid metal transfers the heat it carries to the closed-cycle power generation system through the high-temperature heat exchanger 4, and then the closed-cycle power generation system converts part of the heat into electrical energy. The generated electrical energy is sufficient to meet the electricity needs of the fuel electric pump 2, the liquid metal electromagnetic pump 6 and other equipment; the fuel serves as the cold source and final heat sink of the integrated management system, and the excess heat of the closed-cycle power generation system is transferred to the low-temperature fuel through the cooler 3. The fuel after absorbing heat is passed into the combustion chamber 10 for combustion, forming a heat sink system.

[0026] This application uses liquid metal as a coolant instead of fuel, avoiding the risk of hydrocarbon fuel coking blocking cooling channels and achieving the effect of cooling the entire aircraft. The liquid metal system utilizes the excellent heat transfer capacity of liquid metal to achieve the effect of timely heat transfer. The closed-cycle power generation system uses external work to convert thermal energy into electrical energy for use on the aircraft, reducing heat transfer to the fuel and improving fuel heat sink.

[0027] The outlet of the liquid metal electromagnetic pump 6 is connected to the inlet of the engine wall cooling channel 7 by a pipeline, and an electronic component cooling channel and a skin cooling channel are provided. This design achieves the cooling purpose of the entire machine: cooling the electronic components, cooling the aircraft skin, and cooling the wall of the engine combustion chamber 10.

[0028] The closed-cycle power generation device 5 includes a compressor, a turbine, and a generator. The hot-side outlet of the cooler 3 is connected to the compressor, which is connected to the cold-side inlet of the high-temperature heat exchanger 4. The cold-side outlet of the high-temperature heat exchanger 4 is connected to the turbine inlet, which is connected to the hot-side inlet of the cooler 3. The turbine, compressor, and generator are coaxially arranged. This design forms a closed Brayton cycle power generation system.

[0029] The circulating working medium in the closed cycle power generation device 5 is helium or carbon dioxide.

[0030] The liquid metal is a sodium-potassium alloy or a gallium-indium alloy.

[0031] A combined operation method using the above system, wherein the low-temperature fuel in the fuel tank 1 is transported to the cold side of the cooler 3 through the fuel electric pump 2, and the liquid metal is transported to the cooling channel through the liquid metal electromagnetic pump 6, where it absorbs heat and heats up. The heated liquid metal transfers the heat it carries to the closed-cycle power generation device 5 through the high-temperature heat exchanger 4, and the closed-cycle power generation device 5 converts part of the heat into electrical energy, and the remaining heat is transferred to the low-temperature fuel through the cooler 3. The fuel after absorbing heat is passed into the combustion chamber 10 for combustion.

[0032] The technical solutions provided by the present invention have been described in detail above. Specific examples have been used herein to illustrate the structure and implementation of the present invention. The description of the above embodiments is intended only to help understand the method and core concept of the present invention. At the same time, those skilled in the art will appreciate that the specific implementation and scope of application may vary based on the concept of the present invention. In summary, the contents of this specification should not be construed as limiting the present invention.

Claims

1. A heat sink and closed power generation combined operation system, characterized by: The invention comprises a fuel tank (1), a fuel electric pump (2), a cooler (3), a high-temperature heat exchanger (4), a closed-cycle power generation device (5), a liquid metal electromagnetic pump (6) and a wall cooling channel (7), wherein the fuel electric pump (2) is connected between the outlet of the fuel tank (1) and the cold-side inlet end of the cooler (3) through a pipeline, the cold-side outlet end of the cooler (3) is connected to the injector (9) of the engine through a pipeline, the liquid metal electromagnetic pump (6), the wall cooling channel (7) and the hot side of the high-temperature heat exchanger (4) are sequentially connected through pipelines to form a loop, and the hot side of the cooler (3) and the cold side of the high-temperature heat exchanger (4) are respectively connected to the closed-cycle power generation device (5) through pipelines.

2. The heat sink and closed-loop power generation combined operation system according to claim 1, characterized in that: An electronic component cooling channel and a skin cooling channel are provided between the outlet of the liquid metal electromagnetic pump (6) and the inlet of the engine wall cooling channel (7) via a pipeline connection.

3. A heat sink and closed-loop power generation combined operation system according to claim 1 or 2, characterized in that: The closed-cycle power generation device (5) comprises a compressor, a turbine and a generator, wherein the hot side outlet of the cooler (3) is connected to the compressor, the outlet of the compressor is connected to the cold side inlet of the high-temperature heat exchanger (4), the cold side outlet of the high-temperature heat exchanger (4) is connected to the turbine inlet, and the turbine outlet is connected to the hot side inlet of the cooler (3), and the turbine, compressor and generator are coaxially arranged.

4. The heat sink and closed-loop power generation combined operation system according to claim 3, characterized in that: The circulating working medium in the closed-cycle power generation device (5) is helium or carbon dioxide.

5. The heat sink and closed-loop power generation combined operation system according to claim 1, characterized in that: The liquid metal is a sodium-potassium alloy or a gallium-indium alloy.

6. A method for joint operation using the system according to any one of claims 1 to 5, characterized in that: The low-temperature fuel in the fuel tank (1) is transported to the cold side of the cooler (3) through the fuel electric pump (2), and the liquid metal is transported to the cooling channel through the liquid metal electromagnetic pump (6). After absorbing heat in the cooling channel, the temperature is increased. The heated liquid metal transfers the heat it carries to the closed-cycle power generation device (5) through the high-temperature heat exchanger (4). The closed-cycle power generation device (5) converts part of the heat into electrical energy, and the remaining heat is transferred to the low-temperature fuel through the cooler (3). The fuel after absorbing heat is passed into the combustion chamber (10) for combustion.

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