High-speed aircraft heat dredging-power generation integrated device

Abstract

The invention discloses a high-speed aircraft heat dredging-power generation integrated device which comprises a heat dredging pulsating heat pipe arranged on a nose cone of a high-speed aircraft; the heat dredging pulsating heat pipe comprises an annular pulsating heat pipe condensation section, a plurality of U-shaped pulsating heat pipe evaporation sections and two middle sections, wherein each U-shaped pulsating heat pipe evaporation section is connected with the annular pulsating heat pipe condensation section through the two middle sections. At least one shunting pipeline communicated with the middle sections is arranged between the two middle sections at intervals; the heat extraction pipeline exchanges heat with the annular pulsating heat pipe condensation section of the heat dredging pulsating heat pipe; and the power generation module converts the heat energy obtained by the heat extraction pipeline into electric energy. According to the integrated device, high-temperature aerodynamic heat is converted into electric quantity while thermal protection is carried out on the aircraft, the requirement of the aircraft for an airborne battery power source is relieved, the carrying requirement of a cooling working medium is reduced, the energy utilization rate is increased, and the integrated device has important significance on the aircraft working for a long time in a severe thermal environment.

Description

Technical Field

[0001] The present invention relates to the technical field of thermal protection and heat utilization of aerospace vehicles, and in particular to a high-speed aircraft thermal conduction-power generation integrated device. Background Art

[0002] When a high-speed aircraft is flying in the atmosphere, the aerodynamic heating generated by friction with the incoming atmosphere will cause the temperature of the aircraft's outer surface to rise rapidly, resulting in a decrease in the strength and stiffness of the aircraft structure, threatening the normal operation of the aircraft. For long-term operation, higher requirements are placed on the aircraft's thermal protection measures.

[0003] If a high-speed aircraft in a long-term operation state removes heat through ablation or uses the material's own properties to resist heat, it cannot meet the aircraft's long-term working requirements. At the same time, the aircraft's long-term operation will inevitably require greater battery power. It is more effective to use active thermal protection technologies such as air film cooling and sweat cooling. In addition, the high-temperature heat energy generated by aerodynamic heating is a high-quality energy. The existing thermal protection technology mainly discharges heat from the surface of the aircraft for thermal protection, and cannot effectively utilize the aerodynamic heating heat energy. Among the traditional active cooling methods, only convection cooling can effectively utilize this part of energy. The heat energy is converted into mechanical energy through the circulating working fluid, and the generator is linked to form a thermoelectric conversion system, which uses aerodynamic heat energy to generate electricity, realizing the thermal protection of high-speed aircraft while replacing the power supply required by the aircraft.

[0004] The above-mentioned thermoelectric conversion system can meet the cooling needs of most areas of the aircraft cabin end, but it is difficult to effectively cool the ultra-high temperature components of the aircraft nose cone that are subjected to severe aerodynamic heating. The extreme high temperature of the leading edge of the aircraft nose cone is transferred through the drainage structure and evenly drained to the trailing edge of the aircraft nose cone and the cabin section, which can effectively alleviate the high temperature hazard at the leading edge of the nose cone. Currently, there are few heat drainage solutions applied to the leading edge of the aircraft nose cone, and the main thermal protection technologies are sweat cooling and film cooling, which require carrying more additional cooling media.

[0005] To sum up, there is still room for development in the application of thermal protection measures and aerodynamic heat recovery during the flight of high-speed aircraft. Taking targeted thermal protection methods for different key parts of high-speed aircraft and flexibly and efficiently utilizing the advantages of different thermal protection technologies are effective ways to solve the thermal protection problems of high-speed aircraft under high heat loads, which will promote the development of high-speed aircraft. Summary of the invention

[0006] The technical problem to be solved by the present invention is to propose an integrated device for heat conduction and power generation for high-speed aircraft, which couples the heat conduction technology of convection cooling, thermoelectric conversion and heat pipes. The extreme heat flux at the leading edge of the aircraft nose cone is transferred through the heat pipe, and is gradually conducted to the trailing edge of the aircraft nose cone and the end of the aircraft cabin. The circulating working fluid passes through the heat extraction pipeline on the wall of the aircraft cabin section, and absorbs the high temperature of the wall of the aircraft cabin section and the heat conducted by the heat pipe by convection cooling, and is used for thermoelectric conversion, thereby realizing thermal protection of the aircraft and supplying power to the internal instruments of the aircraft, replacing part of the power source carried by the aircraft. The present invention ensures the safe operation of the high-speed aircraft while using the heat from aerodynamic heating for power generation and power supply, thereby improving energy utilization and providing a feasible idea for the development of related technologies for thermal protection of high-speed aircraft.

[0007] In view of the above technical problems, the specific technical solutions of the present invention are as follows:

[0008] A high-speed aircraft heat conduction-power generation integrated device, comprising:

[0009] A heat conduction pulsating heat pipe is arranged in the nose cone of a high-speed aircraft; the heat conduction pulsating heat pipe comprises an annular pulsating heat pipe condensing section, a plurality of U-shaped pulsating heat pipe evaporating sections and two middle sections connecting each U-shaped pulsating heat pipe evaporating section with the annular pulsating heat pipe condensing section; at least one shunt pipe connected to the middle section is arranged between the two middle sections; liquid plugs and gas plugs are randomly distributed in the heat conduction pulsating heat pipe;

[0010] The heat extraction pipeline is arranged at the rear edge of the nose cone and the wall of the cabin of the high-speed aircraft; and exchanges heat with the annular pulsating heat pipe condensing section of the heat conduction pulsating heat pipe;

[0011] The power generation module is connected to the heat extraction pipeline and converts the heat energy obtained by the heat extraction pipeline into electrical energy.

[0012] The two nodes of the diversion pipeline and the two middle sections are one diversion node and the other confluence node; the diversion pipeline is composed of two arc segments and one straight segment; the bifurcation angle of the node is α, the distance between the two ends of the diversion pipeline is x1, the inner diameter of the arc segment is r1, and the outer diameter of the arc segment is r2; and it should satisfy: 1 / 4*x1 <r2<1 / 3*x1,x2 / 2+r2*sinα<r2。

[0013] Fins are respectively installed on the annular pulsating heat pipe condensing section and the U-shaped pulsating heat pipe evaporating section.

[0014] The heat extraction pipeline adopts a heat exchange channel with a hook-shaped rib array. The working fluid flows through the hook-shaped rib array heat exchange channel to absorb the heat from the surface of the aircraft cabin and the heat from the cold end of the diversion and diversion pulsating heat pipe. The hook-shaped rib array pipeline adds a smooth hook-shaped rib structure in the channel to optimize the number and arrangement of the ribs to form a staggered hook-shaped rib array; the fluid flows through the hook-shaped rib array, the heat exchange area is increased, and when the circulating working fluid flows through the hook-shaped ribs in the channel, a vortex will be formed under the action of the hook structure, generating strong disturbances, and the heat exchange performance is significantly improved.

[0015] The length of the hook rib in the hook rib array is L1, the maximum width of the upper and lower sides is L2, the hook radius is r1, and the height of the hook rib structure is equal to the channel height H1; based on the positioning center of the end of the hook rib structure, the length distance between the hook ribs is L3, and the width distance is L4; and there should be: L1 / 3 3 / 2*L2, L3>3 / 2*L2, and 3 / 4*L2 <r1<5 / 4*L2。 <h1>

[0016] The power generation module includes a generator, a driving pump, a coolant tank, a closed cooling cabin and connecting pipelines; the driving pump is arranged at the inlet of the heat extraction pipeline; the circulating working fluid flows into the heat extraction pipeline under the action of the driving pump, absorbs the heat from the cold end of the heat pipe and the heat from the wall of the aircraft cabin section; the working fluid after absorbing heat is passed into the generator; the cooling medium in the coolant tank is input into the closed cooling cabin, and after cooling the circulating working fluid in the generator, it is transported to the aircraft nose cone for discharge, taking away the heat at the stagnation point of the nose cone, and forming an air film on the outer surface at the tip of the nose cone.

[0017] The generator is a Stirling generator.

[0018] The Stirling generator includes an expansion chamber and a compression chamber, with partition-type high and low temperature heat exchangers and a heat regenerator arranged on both sides; the inlet and outlet of the circulating working fluid are arranged on both sides of the expansion chamber, the inlet end is connected to the outlet of the heat extraction pipeline, the outlet end is connected to the working fluid pump, and is connected to the inlet end of the heat extraction pipeline; the compression chamber is placed in the closed cooling cabin.

[0019] The cooling medium used includes but is not limited to liquid hydrogen, liquid helium, liquid nitrogen, etc.

[0020] The phase change working fluid used in the heat conduction pulsating heat pipe includes but is not limited to water, methanol, ethanol, Freon, difluoromonochloroethane, etc., and the filling rate is 60% to 70%.

[0021] The invention provides a high-speed aircraft heat conduction-power generation integrated device, which combines three technologies: heat pipe, convection cooling and thermoelectric conversion. The extreme heat flow at the leading edge of the aircraft nose cone is transferred along the pulsating heat pipe pipeline to the trailing edge of the aircraft nose cone to the cabin section through the heat conduction effect of the pulsating heat pipe, thereby reducing the high temperature load of the aircraft nose cone and ensuring the safety of operation; the circulating working fluid absorbs the high temperature heat of the aircraft cabin wall through the laid heat extraction pipeline in a convection cooling manner, which is used for thermoelectric conversion, realizing thermal protection while replacing part of the power source carried by the aircraft, thereby improving energy utilization.

[0022] The present invention adopts a Stirling cycle power configuration. The Stirling cycle has good energy recovery efficiency. Under ideal conditions of extreme heat recovery, its cycle thermal efficiency can be equal to the thermal efficiency of the Carnot cycle within the same temperature limit. At the same time, the Stirling cycle power generation system has a compact structure, can burn any fuel or utilize the heat of any heat source, and has strong adaptability. Based on the free piston Stirling generator, high and low temperature heat exchangers and regenerators are added, and a heat exchanger is arranged outside the Stirling generator. The expansion chamber and the compression chamber are connected by a pipeline to exchange heat for the circulating working fluid before and after expansion. The circulating working fluid flows through the heat extraction channel arranged in the cabin section, absorbs heat and expands, passes into the free piston Stirling generator, pushes the piston to do work, and links the engine to generate electricity, thereby realizing the collection and utilization of aerodynamic thermal energy and ensuring the normal operation of the aircraft cabin section.

[0023] In order to improve the heat conduction efficiency of the heat pipe to the extreme heat flow at the leading edge of the aircraft nose cone and ensure the safe operation of the aircraft, the integrated device adopts a convection pulsating heat pipe. On the one hand, fins are installed at the hot and cold ends of the pulsating heat pipe to improve the heat exchange efficiency. On the other hand, convection channels are set between adjacent pipe sections of the pulsating heat pipe to reduce the problems of local stagnation and reverse backflow in the pulsating heat pipe, further improving the heat exchange effect.

[0024] Through the above technical solution, compared with the prior art, the present invention has the following beneficial effects:

[0025] The present invention relates to a high-speed aircraft thermal conduction-power generation integrated device that couples three technologies: heat pipe, convection cooling and thermoelectric conversion. The extreme heat flow at the leading edge of the aircraft nose cone is transferred along the pulsating heat pipe pipeline to the trailing edge of the aircraft nose cone to the cabin section through the thermal conduction effect of the pulsating heat pipe, thereby reducing the high-temperature load of the aircraft nose cone section and ensuring the safety of operation. The circulating working fluid passes through the laid hook-shaped wing rib array heat extraction pipeline to absorb the high-temperature heat of the aircraft cabin section wall in a convection cooling manner for thermoelectric conversion, thereby achieving thermal protection and replacing part of the power source carried by the aircraft, thereby improving energy utilization.

[0026] The present invention relates to a Stirling cycle power configuration; the Stirling cycle has good energy recovery efficiency, and under ideal conditions of extreme heat recovery, its cycle thermal efficiency can be equal to the thermal efficiency of the Carnot cycle within the same temperature limit. The working fluid compatibility and adaptability of the Stirling power generation system applied to aircraft are high, and high-density power working fluid can be used to improve the heat absorption efficiency (improve the cooling efficiency and ensure that the heat on the surface of the aircraft is transferred by the working fluid in time), while ensuring that the system structure is compact and reusable, and reducing the cost required for cooling and utilizing heat; at the same time, the high-temperature and high-pressure circulating working fluid after absorbing heat is further converted into electrical energy through expansion work, realizing the collection and utilization of aerodynamic thermal energy.

[0027] The present invention relates to a convective pulsating heat pipe structure for conducting heat dissipation at the extreme heat flow at the leading edge of a nose cone; the heat at the leading edge of an aircraft nose cone is transported to the cold end along the hot end of the pulsating heat pipe, and during the transportation process, heat is simultaneously released to the trailing edge of the aircraft nose cone and the wall of the aircraft cabin section outside the heat pipe, thereby dissipating the heat at the leading edge of the nose cone to an area less threatened by aerodynamic heat; the integrated device adopts a convective pulsating heat pipe, thereby improving the heat dissipation efficiency of the heat pipe for the extreme heat flow at the leading edge of the aircraft nose cone, thereby ensuring the safe operation of the aircraft; on the one hand, fins are added to the hot end and the cold end of the pulsating heat pipe to improve the heat exchange efficiency, and on the other hand, diversion pipes are provided between adjacent pipe sections of the pulsating heat pipe to reduce problems such as local stagnation and reverse backflow in the pulsating heat pipe, thereby further improving the heat exchange effect.

[0028] The present invention relates to a heat exchange microchannel with a hook-shaped rib array structure having a strong disturbance effect. A hook-shaped rib array is arranged in the heat exchange channel by utilizing a micro-surface processing design, and a circulating medium flows through the heat exchange channel to perform convection heat exchange with a high-temperature wall surface of an aircraft cabin section. Due to the presence of the hook-shaped rib array in the microchannel, more heat exchange surface area is provided, and when the circulating medium flows in the channel, an eddy current is formed under the action of the hook-shaped structure, generating a strong disturbance, thereby improving the heat exchange performance, allowing more heat to be absorbed by the circulating medium, thereby ensuring that the temperature of the aircraft wall surface is within a safe range while improving the power generation capacity of the device.

[0029] The present invention relates to a thermal protection method combining heat conduction and convection cooling; after the cooling medium in the coolant tank and the closed cooling cabin cools the working fluid in the compression chamber of the free piston Stirling generator, it evaporates due to heat and is transported to the stagnation point of the aircraft nose cone along the connecting pipeline, and is discharged to the outside of the aircraft through the porous medium breathable material, taking away the heat at the stagnation point of the nose cone, avoiding heat accumulation inside the aircraft, improving the power generation efficiency of the power generation module, and forming an air film on the outer surface of the tip of the aircraft nose cone, thereby enhancing the thermal protection effect on the stagnation point of the aircraft nose cone.

[0030] Other features and advantages of the present invention will be described in detail in the following detailed description. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] Figure 1 : Schematic diagram of the integrated device for heat conduction and power generation for high-speed aircraft of the present invention;

[0032] Figure 2 : Schematic diagram of the heat conduction shunt pulsating heat pipe structure of the present invention;

[0033] Figure 3 : Figure 2 Plane development of heat conduction and shunt pulsating heat pipe;

[0034] Figure 4 : Schematic diagram of the free piston Stirling generator of the present invention;

[0035] Figure 5 : Schematic diagram of the Stirling cycle thermodynamic process of the present invention: a) PV diagram; b) Ts diagram;

[0036] Figure 6 : Schematic diagram of the heat extraction channel structure of the hook-shaped rib array of the present invention;

[0037] Figure 7 : Figure 6 AA section view;

[0038] Figure 8 : Schematic diagram of heat exchange performance comparison of the edge measuring points of the heat exchange channel of the hook-shaped rib array of the present invention: a) the maximum temperature at the bottom of the heat exchange channel; b) the pressure drop at the inlet and outlet of the heat exchange channel;

[0039] Fig. 9 : Schematic diagram of heat exchange performance comparison of the central measuring point of the heat exchange channel of the hook-shaped rib array of the present invention: a) maximum temperature at the bottom of the heat exchange channel; b) pressure drop at the inlet and outlet of the heat exchange channel.

[0040] In the figure: 1. heat conduction shunt pulsating heat pipe; 101. pulsating heat pipe evaporation section; 102. liquid plug; 103. gas plug; 104. shunt pipe; 105. pulsating heat pipe condensation section; 2. hook-shaped wing rib array taking channel; 201. flow channel inlet; 202. flow channel outlet; 203. hook-shaped wing rib structure; 3. cabin wall; 4. free piston Stirling generator; 401. expansion chamber; 402. high temperature heat exchanger; 403. regenerator; 404. low temperature heat exchanger; 405. compression chamber; 406. magnetic coil motor; 407. leaf spring; 408. power piston; 409. piston rod; 410. phase modulator; 5. drive pump; 6. closed cooling cabin; 7. coolant tank; 8. connecting pipe; 9. porous medium breathable material. DETAILED DESCRIPTION

[0041] In order to deepen the understanding of the present invention, the present invention will be further described in detail below with reference to the accompanying drawings. The embodiments are only used to explain the present invention and do not constitute a limitation on the protection scope of the present invention.

[0042] like Figure 1 As shown, the present invention is a high-speed aircraft heat conduction-power generation integrated device, including a heat conduction pulsating heat pipe 1, a hook-shaped wing rib array heat extraction channel 2, a cabin wall 3, a free piston Stirling generator 4, a drive pump 5, a closed cooling cabin 6, a coolant tank 7 and a connecting pipeline 8; the specific working process of the integrated device is as follows: the extreme heat flow of the leading edge of the nose cone of the high-speed aircraft is discharged along the heat pipe to the trailing edge of the nose cone of the aircraft and the cabin wall 3 through the action of the heat conduction shunt pulsating heat pipe 1, so as to alleviate the high temperature threat of the nose cone; under the action of the drive pump 5, the circulating working fluid is introduced into the The hook-shaped rib array heat extraction channel 2 absorbs heat from the pulsating heat pipe condensation section 105 and the cabin wall 3, and passes it into the free piston Stirling generator 4 to convert thermal energy into mechanical energy; the circulating working fluid after heat exchange re-enters the hook-shaped rib array heat extraction channel 2 to absorb heat and start a new round of circulation; the coolant is passed from the coolant 7 through the connecting pipe 8 into the closed cooling cabin 6, serving as the cold source of the free piston Stirling generator 4, and the heat-absorbing and evaporated cooling medium is passed into the stagnation point at the tip of the aircraft nose cone, and is discharged outward through the porous medium breathable material 9, taking away the extreme heat at the stagnation point and forming an air film to block heat.

[0043] like Figure 2 and Figure 3 As shown, the heat conduction and shunting pulsating heat pipe 1 in the present invention comprises a pulsating heat pipe evaporating section 101, a liquid plug 102, a gas plug 103, a shunting pipe 104 and a pulsating heat pipe condensing section 105; in view of the extreme heat flow at the leading edge of the nose cone of a high-speed aircraft, fins are added to the pulsating heat pipe evaporating section 101 to improve the heat exchange capacity, and the heat at the leading edge of the nose cone is absorbed in time; the working fluid in the pulsating heat pipe evaporating section 101 absorbs heat and evaporates, and flows to the pulsating heat pipe condensing section 105, and there are randomly distributed liquid plugs 102 and Air plug 103, there is a pressure difference between adjacent pipes, the working fluid oscillates between the evaporation end and the condensation end to achieve heat transfer; if only the heat transfer path or heat transfer area of ​​the pulsating heat pipe is increased, the pulsation path of the working fluid will become longer, the pulsation will be weakened, and the effective thermal conductivity will decrease accordingly. Although multiple pulsating heat pipes connected in parallel will not weaken the pulsation effect due to the path, if the working fluid in one group is blocked, it will affect the flow of the working fluid in other pulsating heat pipes connected in parallel, resulting in a decrease in the overall heat transfer coefficient of the pulsating heat pipe. Through the shunt pipe 104, the mainstream of the working medium continues to flow to the condensation section 105 of the pulsating heat pipe, and some liquid plugs 102 or gas plugs 103 that may cause blockage and reflux temporarily enter the shunt pipe 104, reducing the disorder of the distribution of the liquid plugs 102 and gas plugs 103 when the working medium flows in the pipe, reducing possible backflow and blockage of the working medium, improving the circulation flow of the working medium from the evaporation section 101 to the condensation section 105, and improving the heat transfer capacity and stability of the pulsating heat pipe.

[0044] The size characteristics of the diversion pulsating heat pipe are as follows: the bifurcation angle of the diversion pipeline is α, the distance between the two ends of the diversion pipeline is x1, the inner bending diameter is r1, and the outer diameter is r2; and it should satisfy: 1 / 4*x1 < r2 < 1 / 3*x1, x2 / 2 + r2*sinα < r2, to ensure that the working medium is divided into two relatively uniform working media of liquid plug 102 and gas plug 103, and flows to the diversion pipeline and the condensation end of the pulsating heat pipe respectively.

[0045] As Figure 2 shown, the free piston Stirling generator in the present invention includes an expansion chamber 401, a high-temperature heat exchanger 402, a regenerator 403, a low-temperature heat exchanger 404, a compression chamber 405, a magnetic coil motor 406, a leaf spring 407, a power piston 408, a piston rod 409, and a phase shifter 410; the power piston 408 is connected to the leaf spring 407 through the piston rod 409, the magnetic coil motor is arranged around the power piston 408, the compression chamber 405 is arranged between the power piston 408 and the piston rod 409, and the high-temperature regenerator 402, the regenerator 403, and the low-temperature regenerator 404 are arranged in sequence; under the action of the driving pump 5, the high-temperature and high-pressure circulating working medium enters the expansion chamber 401, pushes the gas piston, drives the piston rod 409 and the power piston 408 to move, converts heat energy into mechanical energy, the power piston 408 drives the magnetic coil motor 406 to generate electricity, and the high-temperature heat exchanger 402, the regenerator 403, and the low-temperature heat exchanger 404 exchange heat between the gases on both sides of the expansion chamber 401 and the compression chamber 405 to improve the efficiency of the Stirling generator.

[0046] As Figure 6 、 7 shown, the heat extraction channel of the hook-shaped wing rib array in the present invention includes a flow channel inlet 201, a flow channel outlet 202, and a hook-shaped wing rib structure 203; the hook-shaped wing rib structure 203 is arranged in an array on the lower surface (outer surface) of the heat extraction channel, and the top of the hook-shaped wing rib structure 203 is pressed and overlapped with the upper surface (inner surface) of the heat exchange channel; the presence of the wing-shaped side wall surface of the hook-shaped wing rib structure 203 significantly increases the heat exchange area, the circulating working medium flows into the heat exchange channel through the flow channel inlet 201, generates strong disturbance when flowing through the hook-shaped wing rib structure 203, and forms a vortex in the hook, strengthening the heat exchange effect between the working medium and the wall surface of the high-temperature cabin section, and enhancing the work capacity of the circulating working medium; finally, the circulating working medium flows out through the flow channel outlet 202.

[0047] The dimensional characteristics of the hook-shaped wing rib structure are as follows: the length is L1, and the maximum width of the upper and lower sides is L2; taking the positioning center at the end of the hook-shaped wing rib structure as the reference, the length distance between the hook-shaped wing rib structures is L3, the width distance is L4, the hook radius is r1, the height H1 of the single-layer heat exchange channel is considered according to the actual wall thickness of the aircraft, and the height of the hook-shaped wing rib structure should be equal to the channel height H1. And it should be: L1 / 3 < H1 < L1 / 2, to avoid an overly thick flow boundary layer and insufficient bottom flow around the hook-shaped wing rib structure 203 due to excessive height, which affects the heat exchange effect; L4 > 3 / 2 * L2, L3 > 3 / 2 * L2, to ensure enough space for the flow to fully develop and at the same time reduce the pressure loss when flowing through the hook-shaped wing rib array; 3 / 4 * L2 < r1 < 5 / 4 * L2, to ensure an appropriate hook size, which can help form vortices, enhance the secondary disturbance in the flow, and improve the heat exchange effect.

[0048] The present invention aims to propose an integrated device for efficiently utilizing aerodynamic heat to achieve thermal protection and power generation. By coupling a pulsating heat pipe with a Stirling generator and arranging them in the nose cone and cabin sections respectively, the extreme heat flux at the leading edge of the nose cone is diverted to the trailing edge of the nose cone and the cabin section. The circulating working fluid absorbs heat and does work, which is converted into electrical energy to supply the internal equipment of the aircraft, realizing the recovery and utilization of aerodynamic heat and reducing the consumption of battery power; since the heat in the nose cone part is diverted through the pulsating heat pipe, the required cooling working fluid is eliminated, and the aircraft has more potential when there is a demand for long-endurance operation, and the cost required for repeated operation is lower; with the participation of the optimized heat exchange channels, the performance of the integrated device is improved.

[0049] The above specific embodiments are only for illustrating the technical concept and structural characteristics of the present invention, aiming to enable those skilled in the art to implement it accordingly. However, the above content does not limit the protection scope of the present invention. Any equivalent changes or modifications made according to the spirit and essence of the present invention shall fall within the protection scope of the present invention.

Claims

1. A high-speed aircraft heat conduction-power generation integrated device, characterized in that: include: Heat conduction pulsating heat pipes are arranged in the nose cone of high-speed aircraft; The heat conduction pulsating heat pipe comprises an annular pulsating heat pipe condensing section, a plurality of U-shaped pulsating heat pipe evaporating sections and two middle sections connecting each U-shaped pulsating heat pipe evaporating section with the annular pulsating heat pipe condensing section; at least one shunt pipe connected to the middle section is arranged between the two middle sections; liquid plugs and gas plugs are randomly distributed in the heat conduction pulsating heat pipe; The heat extraction pipeline is arranged at the rear edge of the nose cone and the wall of the cabin of the high-speed aircraft; and exchanges heat with the annular pulsating heat pipe condensing section of the heat conduction pulsating heat pipe; The power generation module is connected to the heat extraction pipeline and converts the heat energy obtained by the heat extraction pipeline into electrical energy.

2. A high-speed aircraft heat conduction-power generation integrated device according to claim 1, characterized in that: The two nodes of the diversion pipeline and the two middle sections are one diversion node and the other confluence node; the diversion pipeline is composed of two arc segments and one straight segment; the bifurcation angle of the node is α, the distance between the two ends of the diversion pipeline is x1, the inner diameter of the arc segment is r1, and the outer diameter of the arc segment is r2; and it should satisfy: 1 / 4*x1 <r2<1 / 3*x1,x2 / 2+r2*sinα<r2。 3. The high-speed aircraft heat conduction-power generation integrated device according to claim 1, characterized in that: Fins are respectively installed on the annular pulsating heat pipe condensing section and the U-shaped pulsating heat pipe evaporating section.

4. The high-speed aircraft heat conduction-power generation integrated device according to claim 1, characterized in that: The heat extraction pipeline adopts a heat exchange channel with a hook-shaped wing rib array. The working fluid flows through the heat exchange channel of the hook-shaped wing rib array to absorb the surface heat of the aircraft cabin and the cold end heat of the diversion and shunt pulsating heat pipe.

5. The high-speed aircraft heat conduction-power generation integrated device according to claim 4, characterized in that: The length of the hook rib in the hook rib array is L1, the maximum width of the upper and lower sides is L2, the hook radius is r1, and the height of the hook rib structure is equal to the channel height H1; based on the positioning center of the end of the hook rib structure, the length distance between the hook ribs is L3, and the width distance is L4; and there should be: L1 / 3 <H1<L1 / 2,L4> 3 / 2*L2, L3>3 / 2*L2, and 3 / 4*L2 <r1<5 / 4*L2。 6. A high-speed aircraft heat conduction-power generation integrated device according to any one of claims 1 to 5, characterized in that: The power generation module includes a generator, a driving pump, a coolant tank, a closed cooling cabin and connecting pipelines; the driving pump is arranged at the inlet of the heat extraction pipeline; the circulating working fluid flows into the heat extraction pipeline under the action of the driving pump, absorbs the heat from the cold end of the heat pipe and the heat from the wall of the aircraft cabin section; the working fluid after absorbing heat is passed into the generator; the cooling medium in the coolant tank is input into the closed cooling cabin, and after cooling the circulating working fluid in the generator, it is transported to the aircraft nose cone for discharge.

7. The high-speed aircraft heat conduction-power generation integrated device according to claim 6, characterized in that: The generator is a Stirling generator.

8. The high-speed aircraft heat conduction-power generation integrated device according to claim 7, characterized in that: The Stirling generator includes an expansion chamber and a compression chamber, with partition-type high and low temperature heat exchangers and a heat regenerator arranged on both sides; the inlet and outlet of the circulating working fluid are arranged on both sides of the expansion chamber, the inlet end is connected to the outlet of the heat extraction pipeline, the outlet end is connected to the working fluid pump, and is connected to the inlet end of the heat extraction pipeline; the compression chamber is placed in the closed cooling cabin.

9. The high-speed aircraft heat conduction-power generation integrated device according to claim 6, characterized in that: The cooling medium used includes but is not limited to liquid hydrogen, liquid helium, and liquid nitrogen.

10. A high-speed aircraft heat conduction-power generation integrated device according to any one of claims 1 to 5, characterized in that: The phase change working fluid used in the heat conduction pulsating heat pipe includes but is not limited to water, methanol, ethanol, Freon, and difluoromonochloroethane, and the filling rate is 60% to 70%.

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