CN117302501A - High-speed aircraft waste heat utilization system and high-speed aircraft based on bionic heat pipe - Google Patents
High-speed aircraft waste heat utilization system and high-speed aircraft based on bionic heat pipe Download PDFInfo
- Publication number
- CN117302501A CN117302501A CN202311114539.5A CN202311114539A CN117302501A CN 117302501 A CN117302501 A CN 117302501A CN 202311114539 A CN202311114539 A CN 202311114539A CN 117302501 A CN117302501 A CN 117302501A
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- China
- Prior art keywords
- heat
- bionic
- heat pipe
- pipe
- speed aircraft
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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- 239000011664 nicotinic acid Substances 0.000 title claims abstract description 53
- 239000002918 waste heat Substances 0.000 title claims abstract description 35
- 239000000446 fuel Substances 0.000 claims description 10
- 238000010438 heat treatment Methods 0.000 claims description 8
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 claims description 4
- 230000035515 penetration Effects 0.000 claims description 4
- 230000000694 effects Effects 0.000 claims description 3
- 229910000838 Al alloy Inorganic materials 0.000 claims description 2
- 229910001069 Ti alloy Inorganic materials 0.000 claims description 2
- 229910052759 nickel Inorganic materials 0.000 claims description 2
- 229910000601 superalloy Inorganic materials 0.000 claims description 2
- 239000000956 alloy Substances 0.000 claims 2
- 238000010030 laminating Methods 0.000 claims 1
- 230000008901 benefit Effects 0.000 abstract description 3
- 238000011084 recovery Methods 0.000 abstract description 2
- 239000007788 liquid Substances 0.000 description 13
- 239000011148 porous material Substances 0.000 description 9
- 238000002407 reforming Methods 0.000 description 7
- 239000000463 material Substances 0.000 description 5
- 238000001816 cooling Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 238000005245 sintering Methods 0.000 description 3
- 230000001133 acceleration Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 2
- 230000005484 gravity Effects 0.000 description 2
- 239000007921 spray Substances 0.000 description 2
- 230000005540 biological transmission Effects 0.000 description 1
- 239000011248 coating agent Substances 0.000 description 1
- 238000000576 coating method Methods 0.000 description 1
- 238000009833 condensation Methods 0.000 description 1
- 230000005494 condensation Effects 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000001704 evaporation Methods 0.000 description 1
- 230000008020 evaporation Effects 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 230000017525 heat dissipation Effects 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 230000036544 posture Effects 0.000 description 1
- 230000002277 temperature effect Effects 0.000 description 1
- 239000002699 waste material Substances 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/38—Constructions adapted to reduce effects of aerodynamic or other external heating
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C30/00—Supersonic type aircraft
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/78—Other construction of jet pipes
- F02K1/82—Jet pipe walls, e.g. liners
- F02K1/822—Heat insulating structures or liners, cooling arrangements, e.g. post combustion liners; Infrared radiation suppressors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C2001/0054—Fuselage structures substantially made from particular materials
- B64C2001/0081—Fuselage structures substantially made from particular materials from metallic materials
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- General Engineering & Computer Science (AREA)
- Heat-Exchange Devices With Radiators And Conduit Assemblies (AREA)
Abstract
The invention discloses a high-speed aircraft waste heat utilization system based on a bionic heat pipe, which comprises a skin and a tail nozzle, wherein a simulated heat pipe group is arranged on the inner surface of the skin and the outer surface of the tail nozzle, the bionic heat pipe group comprises a plurality of bionic heat pipes, the shape of each bionic heat pipe is attached to the inner surface of the skin or the outer surface of the tail nozzle, the bionic heat pipes are connected with a waste heat utilization device, and the waste heat utilization device recovers heat of the skin and the wall of the tail nozzle through the bionic heat pipes. The bionic heat pipe absorbs heat of the skin, the tail nozzle and the like and performs waste heat recovery, so that the heat is effectively recovered while the high-temperature part is protected, and the bionic heat pipe is energy-saving, environment-friendly and high in economic benefit.
Description
Technical Field
The invention relates to a hypersonic aircraft, in particular to a bionic heat pipe-based high-speed aircraft waste heat utilization system and a high-speed aircraft.
Background
Physical phenomena such as stagnation point deflection, high temperature effects, low density flow, thin impact layers, viscous interactions, entropy layers and the like exist in the flight process of the hypersonic aircraft. The high-speed aircraft skin plays a role in bearing and transmitting aerodynamic loads while forming the aerodynamic profile of the aircraft. The skin has a severe working environment and complex stress, so the skin material is required to have high strength, good plasticity, smooth surface and strong corrosion resistance. In the ultra-high speed flight process of an aircraft, the temperature of the skin can reach above 1000K, and direct heat dissipation to the atmosphere is considered to be extremely wasteful. The high temperature and pressure fuel gas flowing out of the turbine of the aircraft continues to expand in the tail pipe and is discharged from the nozzle backwards along the axial direction of the engine at a high speed. This velocity is much greater than the velocity of the air stream entering the engine, allowing the engine to obtain reactive thrust. This process also causes a significant amount of heat to be generated by the nozzle wall. The high temperatures not only place higher demands on the cooling of the aircraft, but also lead to energy waste.
Disclosure of Invention
The invention aims to: aiming at the defects, the invention provides a bionic heat pipe-based high-speed aircraft waste heat utilization system which can protect high-temperature components such as a skin, a tail pipe and the like and simultaneously utilize waste heat.
The technical scheme is as follows: in order to solve the problems, the invention adopts the high-speed aircraft waste heat utilization system based on the bionic heat pipes, the high-speed aircraft comprises a skin and a tail nozzle, the inner surface of the skin and the outer surface of the tail nozzle are provided with the heat simulating pipe groups, the bionic heat pipe groups comprise a plurality of bionic heat pipes, the shapes of the bionic heat pipes are attached to the inner surface of the skin or the outer surface of the tail nozzle, the bionic heat pipes are connected with waste heat utilization devices, and the waste heat utilization devices recover heat of the skin and the wall of the tail nozzle through the bionic heat pipes.
Furthermore, the number of the bionic heat pipes at the high heating position of the inner surface of the skin or the outer surface of the tail nozzle is more than that at the low heating position. The bionic heat pipe adopts a micro-channel heat pipe or a porous sintering heat pipe.
Further, the waste heat utilization device comprises a fuel reforming device, and the bionic heat pipe is used for transferring heat of the inner surface of the skin and the outer surface of the tail nozzle to the fuel reforming device and supplying heat to the fuel reforming device.
The beneficial effects are that: compared with the prior art, the invention has the remarkable advantages that the bionic heat pipe absorbs heat of the skin, the tail nozzle and the like and carries out waste heat recovery, so that the high-temperature part is protected, the heat is effectively recovered, the energy is saved, the environment is protected, the economic benefit is high, and meanwhile, the bionic special-shaped heat pipe attached to the inner surface of the skin or the outer surface of the tail nozzle is adopted, so that the cooling effect of a flight platform in high-speed flight is improved. Under the acceleration condition, the aircraft forms a high penetration physical field, the heat transport capacity of the bionic heat pipe is improved, and the cooling effect is further improved.
Drawings
FIG. 1 is a schematic diagram of a waste heat utilization system according to the present invention.
Detailed Description
As shown in fig. 1, a high-speed aircraft waste heat utilization system based on a bionic heat pipe in this embodiment includes a simulated heat pipe group disposed on an inner surface of a skin and an outer surface of a tail pipe of the high-speed aircraft, and a waste heat utilization device connected with the bionic heat pipe group, wherein the bionic heat pipe group includes a plurality of bionic heat pipes, the bionic heat pipes adopt fine circulation channels for driving fluid to circulate in a closed channel for heat exchange by thermal driving force under a full physical force field, the shape of the bionic heat pipes is attached to the inner surface of the skin or the outer surface of the tail pipe, and the quantity of the bionic heat pipes at high heating positions of the inner surface of the skin and the outer surface of the tail pipe is more than that at low heating positions, the bionic heat pipes are connected with the waste heat utilization device, and the waste heat utilization device recovers heat of the skin and the wall of the tail pipe through the bionic heat pipes. When the temperature of the liquid working medium of the bionic heat pipe closed metal pipeline is higher, the liquid working medium absorbs the heat of the skin or the tail nozzle, the steam is transmitted to a waste heat utilization device in the pipeline, the waste heat utilization device collects the heat, the working medium is condensed into liquid, and the liquid flows back to the end of the skin or the tail nozzle through the capillary action of the liquid suction core. The waste heat utilization device comprises a fuel reforming device, and the bionic heat pipe is used for transferring heat of the inner surface of the skin and the outer surface of the tail nozzle to the fuel reforming device and supplying heat of the fuel reforming device. The fuel reforming device is connected with the fuel cell.
The bionic heat pipe adopts a micro-channel heat pipe (Microgroove Heat Pipe) or a porous sintered heat pipe (Porous Sintered Heat Pipe). The micro-channel heat pipe has a micro-channel or groove structure inside the pipe to enhance the heat transfer performance and thermal management capability of the heat pipe. The existence of the micro-channel increases the surface area inside the pipeline, improves the heat conduction efficiency of the heat pipe, and ensures that more heat can be absorbed and transferred; the micro-channels can help the liquid to be distributed more uniformly in the heat pipe, so that the phenomenon that the liquid is nonuniform in the pipeline is avoided, and the heat transfer efficiency is improved; the micro-channel structure is beneficial to reducing the thermal resistance between the liquid and the pipeline wall, thereby reducing the resistance of heat conduction and improving the heat transfer performance; the micro-channel heat pipe can effectively transfer heat in different directions due to the optimized internal structure, and is not influenced by gravity; the compact structure of the microchannel heat pipe enables it to accommodate limited space.
The porous sintered heat pipe adopts porous sintered materials in the pipeline to realize heat conduction. Porous sintered heat pipes utilize evaporation and condensation of a liquid to transfer heat by injecting a liquid working medium into the pores of a porous material. The porous sintered heat pipe uses special porous materials to replace the inner wall coating or film in the traditional heat pipe. These porous materials generally have a high degree of thermal conductivity and good wettability, enabling the liquid to be uniformly distributed in the pores and to flow inside the pores by capillary action. The porous sintered material has higher heat conductivity, can effectively conduct heat and improve the heat conductivity of the heat pipe; the pore structure of the porous material can help the liquid to be uniformly distributed in the interior, so that the heat transfer efficiency of the heat pipe is improved; the liquid transmission of the porous sintering heat pipe is not affected by gravity, and the porous sintering heat pipe is suitable for different postures and environments; the porous material can be adjusted according to different application requirements to meet different thermal management requirements.
The high-speed aircraft skin material is aluminum alloy or titanium alloy, and plays a role in bearing and transmitting aerodynamic load while forming the aerodynamic profile of the aircraft. The tail spray pipe is a Laval spray pipe, and the material is nickel-based superalloy. The bionic heat pipe absorbs heat of the skin, the tail jet pipe and the like, so that on one hand, the high-temperature components are protected, and on the other hand, the heat can be effectively recovered. And under the acceleration condition, a high penetration force field is formed, and the heat transport capacity of the heat pipe is further improved.
In a cruise state of the high-speed aircraft, the skin heat pipe does not work, and the tail pipe heat pipe works; the high-speed aircraft is in a high forward penetration physical state, the skin heat pipe works, and the tail pipe heat pipe works; the aircraft Gao Fuxiang is in a physical state, the skin heat pipe does not work, and the tail pipe heat pipe works.
Claims (10)
1. The utility model provides a high-speed aircraft waste heat utilization system based on bionical heat pipe, high-speed aircraft includes skin and tail pipe, its characterized in that, skin internal surface and tail pipe surface have laid imitative heat nest of tubes, bionical heat nest of tubes includes a plurality of bionical heat pipes, bionical heat pipe's shape laminating skin internal surface or tail pipe surface, bionical heat pipe all is connected with waste heat utilization device, and waste heat utilization device retrieves the heat of skin and tail pipe wall through bionical heat pipe.
2. The high-speed aircraft waste heat utilization system based on the bionic heat pipes according to claim 1, wherein the number of the bionic heat pipes at the high heating position of the inner surface of the skin is larger than the number of the bionic heat pipes at the low heating position.
3. The high-speed aircraft waste heat utilization system based on the bionic heat pipes according to claim 1, wherein the number of the bionic heat pipes at the high heating position of the outer surface of the tail nozzle is greater than the number of the bionic heat pipes at the low heating position.
4. The high-speed aircraft waste heat utilization system based on the bionic heat pipe according to claim 1, wherein the bionic heat pipe is a micro-channel heat pipe.
5. The high-speed aircraft waste heat utilization system based on the bionic heat pipe according to claim 1, wherein the bionic heat pipe is a porous sintered heat pipe.
6. The bionic heat pipe-based high-speed aircraft waste heat utilization system according to claim 4, wherein when the high-speed aircraft accelerates to form a high penetration body force field, the thermal driving force effect of driving working medium to circularly flow in the bionic heat pipe is enhanced.
7. The high-speed aircraft waste heat utilization system based on the bionic heat pipe according to claim 1, wherein the skin is made of an aluminum alloy material or a titanium alloy material.
8. The bionic heat pipe-based high-speed aircraft waste heat utilization system according to claim 1, wherein the tail nozzle is a Laval nozzle, and the tail nozzle is made of nickel-based superalloy.
9. A high-speed aircraft waste heat utilization system based on a bionic heat pipe according to claim 2 or 3, wherein the waste heat utilization device comprises a fuel reformer to which the bionic heat pipe transfers heat from the inner surface of the skin and the outer surface of the tail pipe for heat supply of the fuel reformer.
10. A high speed aircraft comprising a waste heat utilization system according to any one of claims 1 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311114539.5A CN117302501A (en) | 2023-08-31 | 2023-08-31 | High-speed aircraft waste heat utilization system and high-speed aircraft based on bionic heat pipe |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311114539.5A CN117302501A (en) | 2023-08-31 | 2023-08-31 | High-speed aircraft waste heat utilization system and high-speed aircraft based on bionic heat pipe |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117302501A true CN117302501A (en) | 2023-12-29 |
Family
ID=89245325
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311114539.5A Pending CN117302501A (en) | 2023-08-31 | 2023-08-31 | High-speed aircraft waste heat utilization system and high-speed aircraft based on bionic heat pipe |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117302501A (en) |
-
2023
- 2023-08-31 CN CN202311114539.5A patent/CN117302501A/en active Pending
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|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |