CN112833685A - Spiral winding pipe air-oil heat exchanger suitable for aeroengine - Google Patents
Spiral winding pipe air-oil heat exchanger suitable for aeroengine Download PDFInfo
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- CN112833685A CN112833685A CN202110008180.8A CN202110008180A CN112833685A CN 112833685 A CN112833685 A CN 112833685A CN 202110008180 A CN202110008180 A CN 202110008180A CN 112833685 A CN112833685 A CN 112833685A
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- annular
- pipe
- spiral winding
- heat exchanger
- air
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F28—HEAT EXCHANGE IN GENERAL
- F28D—HEAT-EXCHANGE APPARATUS, NOT PROVIDED FOR IN ANOTHER SUBCLASS, IN WHICH THE HEAT-EXCHANGE MEDIA DO NOT COME INTO DIRECT CONTACT
- F28D1/00—Heat-exchange apparatus having stationary conduit assemblies for one heat-exchange medium only, the media being in contact with different sides of the conduit wall, in which the other heat-exchange medium is a large body of fluid, e.g. domestic or motor car radiators
- F28D1/02—Heat-exchange apparatus having stationary conduit assemblies for one heat-exchange medium only, the media being in contact with different sides of the conduit wall, in which the other heat-exchange medium is a large body of fluid, e.g. domestic or motor car radiators with heat-exchange conduits immersed in the body of fluid
- F28D1/04—Heat-exchange apparatus having stationary conduit assemblies for one heat-exchange medium only, the media being in contact with different sides of the conduit wall, in which the other heat-exchange medium is a large body of fluid, e.g. domestic or motor car radiators with heat-exchange conduits immersed in the body of fluid with tubular conduits
- F28D1/047—Heat-exchange apparatus having stationary conduit assemblies for one heat-exchange medium only, the media being in contact with different sides of the conduit wall, in which the other heat-exchange medium is a large body of fluid, e.g. domestic or motor car radiators with heat-exchange conduits immersed in the body of fluid with tubular conduits the conduits being bent, e.g. in a serpentine or zig-zag
- F28D1/0472—Heat-exchange apparatus having stationary conduit assemblies for one heat-exchange medium only, the media being in contact with different sides of the conduit wall, in which the other heat-exchange medium is a large body of fluid, e.g. domestic or motor car radiators with heat-exchange conduits immersed in the body of fluid with tubular conduits the conduits being bent, e.g. in a serpentine or zig-zag the conduits being helically or spirally coiled
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
- F02C7/14—Cooling of plants of fluids in the plant, e.g. lubricant or fuel
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F28—HEAT EXCHANGE IN GENERAL
- F28F—DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION
- F28F1/00—Tubular elements; Assemblies of tubular elements
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F28—HEAT EXCHANGE IN GENERAL
- F28F—DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION
- F28F21/00—Constructions of heat-exchange apparatus characterised by the selection of particular materials
- F28F21/08—Constructions of heat-exchange apparatus characterised by the selection of particular materials of metal
- F28F21/081—Heat exchange elements made from metals or metal alloys
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F28—HEAT EXCHANGE IN GENERAL
- F28F—DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION
- F28F9/00—Casings; Header boxes; Auxiliary supports for elements; Auxiliary members within casings
- F28F9/26—Arrangements for connecting different sections of heat-exchange elements, e.g. of radiators
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Heat-Exchange Devices With Radiators And Conduit Assemblies (AREA)
Abstract
The invention discloses a spiral winding pipe air-oil heat exchanger suitable for an aircraft engine, which comprises a first annular main pipe, a second annular main pipe and a spiral winding pipe assembly, wherein the first annular main pipe is connected with the second annular main pipe through a first connecting pipe; the second annular manifold is coaxially arranged in front of the first annular manifold in a front-rear direction at a spacing; a plurality of spiral winding pipe subassemblies are circumference interval-spaced and are radial arrangement on first annular house steward and second annular house steward, a plurality of spiral winding pipe subassemblies spiral winding arrange and form the loop column shape and parallelly connected intercommunication between first annular house steward and second annular house steward, thereby make aviation kerosene get into behind the first annular house steward from the oil inlet, a plurality of spiral winding pipe subassemblies of flowing through respectively, assemble in second annular house steward again, discharge and finally get into the combustion chamber and burn from the oil-out, and high temperature high-pressure air is carried out the heat transfer and is cooled off by a plurality of spiral winding pipe subassemblies of sweepping backward and aviation kerosene. The invention has compact structure, good heat exchange effect, improved energy utilization rate and wide application range.
Description
Technical Field
The invention relates to the technical field of aircraft engine cooling, in particular to a spiral winding pipe air-oil heat exchanger suitable for an aircraft engine.
Background
To improve the efficiency and thrust of an aircraft engine, cooling of the engine is important. With the further increase of the performance requirements of the engine, the engine is required to have higher turbine-front temperature and larger pressure increase ratio, the larger pressure increase ratio means that the cooling quality of high-pressure air for cooling is reduced, and the cooling of hot end parts of the engine is more challenging, and according to technical statistics, the turbine-front temperature is increased by 22K on average per year, wherein the temperature is increased by 8K on average per year by means of the increase of temperature-resistant materials, and the rest 14K is solved by heat transfer workers. The cooling technology has important significance for improving the cycle efficiency of the aircraft engine, increasing the working reliability and prolonging the service life of the whole machine.
The arrangement of the air-oil heat exchanger in the aircraft engine is a scheme with a very wide application prospect. Before aviation kerosene is combusted, the heat can be absorbed physically and chemically through the air-oil heat exchanger, the temperature of high-pressure cooling air is reduced, the cooling quality of the aviation kerosene is improved, and meanwhile, high-energy micromolecule products generated by chemical reaction release absorbed heat through combustion in the combustion chamber, so that the cooling efficiency is improved, and the utilization rate of energy is improved. The heat exchanger disposed on the aircraft engine cannot be directly applied to the aircraft engine because the heat exchanger has a limit to the volume and weight of the heat exchanger.
Disclosure of Invention
The present invention is directed to solving at least one of the problems of the prior art. Therefore, one purpose of the invention is to provide a spiral winding pipe air-oil heat exchanger suitable for an aircraft engine, which has the advantages of compact structure, high space utilization rate, good heat exchange effect, capability of effectively improving the cooling quality of high-temperature and high-pressure air, capability of improving the utilization rate of energy, and wide application range.
According to the embodiment of the invention, the air-oil heat exchanger with the spirally wound pipes suitable for the aircraft engine comprises:
the first annular main pipe is provided with an oil inlet;
the second annular main pipe is provided with an oil outlet, the second annular main pipe and the first annular main pipe are coaxially arranged in a spaced manner in the front-rear direction, and the second annular main pipe is positioned in front of the first annular main pipe;
the spiral winding pipe assemblies are arranged in a spiral winding mode to form a cylindrical shape and are communicated between the first annular main pipe and the second annular main pipe in parallel, so that aviation kerosene flows through the spiral winding pipe assemblies respectively after entering the first annular main pipe from the oil inlet, then flows through the spiral winding pipe assemblies and is gathered in the second annular main pipe, is discharged from the oil outlet and finally enters the combustion chamber for combustion, and high-temperature and high-pressure air is cooled by the forward and backward transverse sweeping of the spiral winding pipe assemblies after being cooled.
The spiral winding pipe air-oil heat exchanger applicable to the aero-engine provided by the embodiment of the invention has the following advantages: firstly, the spiral winding pipe air-oil heat exchanger is in a circular cylindrical shape as a whole, so that the spiral winding pipe air-oil heat exchanger can be conveniently arranged in an annular space inside an aircraft engine, and the utilization rate of the internal space of the aircraft engine is improved; secondly, when the air-oil heat exchanger with the spiral winding pipes works, aviation kerosene RP-3 carried by an aircraft and having the temperature of 330K and the pressure of 5MPa enters the first annular main pipe from the oil inlet, respectively flows through the spiral winding pipe assemblies and then converges in the second annular main pipe, when high-temperature high-pressure air with the temperature of 900K and the pressure of 3MPa sweeps the spiral winding pipe assemblies from front to back, as the critical temperature of the aviation kerosene is 645.5K and the critical pressure is 2.390MPa, the aviation kerosene in the air-oil heat exchanger with the spiral winding pipes is in a supercritical pressure state, when the aviation kerosene with the supercritical pressure is near a quasi-critical temperature, the thermal properties of the aviation kerosene are changed violently and have a large specific heat value, and simultaneously have the diffusion rate of gas and the viscosity and density of liquid, therefore, the heat absorption capacity of the aviation kerosene is strong, and the heat exchange effect between the high-temperature high-pressure air and the aviation kerosene is good, the temperature of high-temperature and high-pressure air can be effectively reduced; thirdly, in the air-oil heat exchanger with the spiral winding pipe, the aviation kerosene flows from back to front on the whole, the high-temperature and high-pressure air flows from front to back, the flowing direction of the aviation kerosene in the spiral pipeline assembly is continuously changed, and secondary circulation is generated in the radial direction, so that the heat transfer of the spiral winding pipe assembly is enhanced, the heat transfer coefficient is improved, and the heat exchange efficiency of the air-oil heat exchanger with the spiral winding pipe is further improved; fourthly, after heat exchange is finished, the aviation kerosene is discharged from the oil outlet and finally enters the combustion chamber to be combusted to release absorbed heat, so that the utilization rate of energy can be effectively improved, and the cooled high-temperature and high-pressure air cools the hot end part of the aero-engine, so that the cooling efficiency can be effectively improved; fifthly, the air-oil heat exchanger with the spiral winding pipe suitable for the aircraft engine is suitable for various aircraft engines, such as a turbojet engine, a turbofan engine, a ramjet engine, a turbo-ram combined engine, a rocket-ram combined engine, a turbo-rocket-ram combined engine and an air-breathing precooling engine, and is wide in application range.
According to one embodiment of the invention, one or more of said oil inlets; one or more oil outlets are arranged.
According to one embodiment of the invention, the helically wound tube assembly is made of an alloy material.
According to one embodiment of the invention, each of the helically wound pipe assemblies comprises a first leg, a second leg and a plurality of helically wound pipes, the first leg extending in a radial direction and communicating with the first annular manifold; the second branch pipe extends in a radial direction and communicates with the second annular manifold; one ends of the spiral winding pipes are respectively paved in a row in the radial direction and are respectively communicated with the first branch pipes, and the other ends of the spiral winding pipes are respectively paved in a row in the radial direction and are respectively communicated with the second branch pipes.
According to a further embodiment of the invention, the first branch is in communication with the first annular manifold via a first connection pipe and the second branch is in communication with the second annular manifold via a second connection pipe.
According to a still further embodiment of the present invention, the first connecting pipe and the second connecting pipe are both porous flat pipes.
According to a further embodiment of the present invention, the porous flat tube includes a plurality of tube holes independent from each other and parallel to each other, and the flow directions of the aviation kerosene in the plurality of tube holes of the same porous flat tube are the same.
According to a further embodiment of the present invention, the first legs of the plurality of spiral wound tube assemblies are evenly spaced and the second legs of the plurality of spiral wound tube assemblies are evenly spaced.
According to a further embodiment of the present invention, the plurality of helically wound tubes in each helically wound tube assembly are evenly spaced.
According to a further embodiment of the present invention, said first annular manifold is located at an outer end of said first legs of said plurality of spiral wound tubular assemblies; the second annular manifold is located at an outer end of the second legs of the plurality of spiral wound coil assemblies.
Additional aspects and advantages of the invention will be set forth in part in the description which follows and, in part, will be obvious from the description, or may be learned by practice of the invention.
Drawings
The above and/or additional aspects and advantages of the present invention will become apparent and readily appreciated from the following description of the embodiments, taken in conjunction with the accompanying drawings of which:
fig. 1 is a schematic perspective view of a spiral wound tube air-oil heat exchanger suitable for an aircraft engine according to an embodiment of the present invention.
FIG. 2 is an axial side view of a helically wound tube air-to-oil heat exchanger suitable for use in an aircraft engine in accordance with an embodiment of the present invention.
Fig. 3 is a partial structural schematic diagram of a spiral wound tube air-oil heat exchanger suitable for an aircraft engine according to an embodiment of the invention.
Fig. 4 is an assembly view of a first annular manifold, a first branch pipe and a first connecting pipe of the air-oil heat exchanger with the spirally-wound pipes suitable for the aircraft engine according to the embodiment of the invention.
Reference numerals:
spiral wound tube air-to-oil heat exchanger 1000
Helically wound pipe assembly 3
Detailed Description
Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the accompanying drawings are illustrative only for the purpose of explaining the present invention, and are not to be construed as limiting the present invention.
A spiral wound tube air-oil heat exchanger 1000 suitable for use in an aircraft engine according to an embodiment of the present invention is described below with reference to fig. 1 to 4.
As shown in fig. 1 to 4, a spiral wound tube air-oil heat exchanger 1000 suitable for an aircraft engine according to an embodiment of the present invention includes a first annular manifold 1, a second annular manifold 2, and a spiral wound tube assembly 3; an oil inlet 11 is formed in the first annular main pipe 1; an oil outlet 21 is formed in the second annular header pipe 2, the second annular header pipe 2 and the first annular header pipe 1 are coaxially arranged at a spacing in the front-rear direction, and the second annular header pipe 2 is positioned in front of the first annular header pipe 1; spiral winding pipe assembly 3 has a plurality ofly, the front end and the rear end of a plurality of spiral winding pipe assemblies 3 are circumference interval and are radial arrangement on first annular house steward 1 and second annular house steward 2, a plurality of spiral winding pipe assemblies 3 spiral winding arrange and form the loop column shape and parallelly connected intercommunication between first annular house steward 1 and second annular house steward 2, thereby make aviation kerosene get into behind first annular house steward 1 from oil inlet 11, flow through a plurality of spiral winding pipe assemblies 3 respectively, assemble in second annular house steward 2 again, discharge and finally get into the combustion chamber from oil-out 21 and burn, and high temperature high-pressure air is cooled off aeroengine's hot end part by a plurality of spiral winding pipe assemblies 3 of sweepforward back after by cooling.
The air-oil heat exchanger 1000 with the spiral winding pipes, which is suitable for the aircraft engine, provided by the embodiment of the invention, has the following advantages: firstly, the spiral winding pipe air-oil heat exchanger 1000 is in a circular cylindrical shape as a whole, and can be conveniently installed in an annular space inside an aircraft engine, so that the utilization rate of the internal space of the aircraft engine is improved; secondly, when the air-oil heat exchanger 1000 with the spiral winding pipes works, the temperature carried by the aircraft is 330K, the aviation kerosene RP-3 with the pressure of 5MPa enters the first annular main pipe 1 from the oil inlet 11, flows through the spiral winding pipe assemblies 3 respectively, and then is converged in the second annular main pipe 2, when high-temperature high-pressure air with the temperature of 900K and the pressure of 3MPa passes through the spiral winding pipe assemblies 3 in a forward and backward transverse mode, because the critical temperature of the aviation kerosene is 645.5K and the critical pressure is 2.390MPa, at the moment, the aviation kerosene in the air-oil heat exchanger 1000 with the spiral winding pipes is in a supercritical pressure state, when the aviation kerosene with the supercritical pressure is near a quasi-critical temperature, the heat of the aviation kerosene is changed violently and has a large value, and simultaneously has the diffusion rate of gas and the viscosity and the physical property of liquid, so that the heat absorption capacity of the aviation kerosene is strong, the heat exchange effect between the high-temperature high-pressure air and the aviation kerosene is good, and the temperature of the high-temperature high-pressure air can be effectively reduced; thirdly, in the spiral wound tube air-oil heat exchanger 1000, aviation kerosene generally flows from back to front, high-temperature and high-pressure air flows from front to back, the flowing direction of the aviation kerosene in the spiral wound tube assembly 3 is continuously changed, and secondary circulation is generated in the radial direction, so that the heat transfer of the spiral wound tube assembly 3 is enhanced, the heat transfer coefficient is improved, and the heat exchange efficiency of the spiral wound tube air-oil heat exchanger 1000 is further improved; fourthly, after heat exchange is finished, the aviation kerosene is discharged from the oil outlet 21 and finally enters the combustion chamber to be combusted to release absorbed heat, so that the utilization rate of energy can be effectively improved, and the cooled high-temperature and high-pressure air cools the hot end part of the aero-engine, so that the cooling efficiency can be effectively improved; fifthly, the air-oil heat exchanger 1000 with the spiral winding pipe suitable for the aircraft engine according to the embodiment of the invention is suitable for various aircraft engines, such as a turbojet engine, a turbofan engine, a ramjet engine, a turbo-ramjet combined engine, a rocket-ramjet combined engine, a turbo-rocket ramjet combined engine and an air-breathing precooling engine, and has a wide application range.
According to one embodiment of the invention, the oil inlets 11 are one or more; one or more oil outlets 21 are provided. It can be understood that, through set up a plurality of oil inlets 11 on first annular manifold 1, set up a plurality of oil-out 21 at second annular manifold 2, can reduce the velocity of flow of aviation kerosene in first annular manifold 1 and second annular manifold 2, reduce the pressure loss, guarantee simultaneously that the flow distribution of aviation kerosene is even in first annular manifold 1 and second annular manifold 2, improve the heat transfer effect.
According to one embodiment of the invention, the helically wound tube assembly 3 is made of an alloy material. Thus, the spirally wound tube assembly 3 has high structural strength and good thermal conductivity, and for example, the spirally wound tube assembly 3 may be made of nickel-chromium alloy.
According to one embodiment of the invention, each helically wound pipe assembly 3 comprises a first branch pipe 31, a second branch pipe 32 and a plurality of helically wound pipes 33, the first branch pipe 31 extending in a radial direction and communicating with the first annular manifold 1; the second branch pipes 32 extend in the radial direction and communicate with the second annular manifold 2; one ends of the plurality of spirally wound pipes 33 are respectively laid out in a row in the radial direction and are respectively communicated with the first branch pipes 31, and the other ends of the plurality of spirally wound pipes 33 are respectively laid out in a row in the radial direction and are respectively communicated with the second branch pipes 32. It can be understood that by arranging the first branch pipe 31 and the second branch pipe 32 in the radial direction, a plurality of spirally wound pipes 33 can be conveniently spread in a row in the radial direction, and two ends of the spirally wound pipes are respectively communicated with the first annular header pipe 1 and the second annular header pipe 2, so that the structure is reasonable and the arrangement is convenient; confirm the quantity of spiral winding pipe assembly 3, the quantity of spiral winding pipe 33 in each spiral winding pipe assembly 3, spiral winding pipe 33 in axial direction interval and the ascending interval of longitudinal direction according to actual conditions to guarantee that a plurality of spiral winding pipe assemblies 3 are rational in infrastructure, avoid taking place space interference, compact structure, thereby increased the heat transfer volume of spiral winding pipe air-oil heat exchanger 1000 unit mass.
It should be noted that the winding manner of the spiral winding tube 33 can be clockwise same-direction winding, counterclockwise same-direction winding or cross winding; the mode of the high-temperature and high-pressure air transversely sweeping the plurality of spiral winding pipe assemblies 3 can be a transversely sweeping parallel-row spiral pipe bundle or a transversely sweeping staggered-row spiral pipe bundle; because the disturbance of the air side in the transverse cross row tube bundle is stronger than that in the transverse parallel row spiral tube bundle, preferably, the mode that the high-temperature high-pressure air transversely sweeps the plurality of spiral winding tube assemblies 3 is the transverse cross row spiral tube bundle, so that the heat exchange coefficient of the spiral winding tube air-oil heat exchanger 1000 is larger, and the size of the heat exchanger is smaller under the condition of the same heat exchange amount.
According to a further embodiment of the invention, the first branch 31 communicates with the first annular manifold 1 through a first connection pipe 34 and the second branch 32 communicates with the second annular manifold 2 through a second connection pipe 35. In this way, the first branch pipe 31 can be conveniently communicated with the first annular main pipe 1, and the second branch pipe 32 can be conveniently communicated with the second annular main pipe 2, and the structure is simple and reasonable.
According to a still further embodiment of the present invention, the first connection pipe 34 and the second connection pipe 35 are both porous flat pipes.
According to a further embodiment of the invention, the porous flat tube comprises a plurality of tube holes which are independent from each other and parallel, and the flow directions of the aviation kerosene in the plurality of tube holes of the same porous flat tube are consistent.
It can be understood that, through set up porous flat pipe between first branch pipe 31 and first ring manifold 1, set up porous flat pipe between second branch pipe 32 and second ring manifold 2, can increase the cross-sectional area that first connecting pipe 34 department aviation kerosene passes through and the cross-sectional area that second connecting pipe 35 department aviation kerosene passes through, reduce the velocity of flow of aviation kerosene in first connecting pipe 34 and second connecting pipe 35, reduce the pressure loss, guarantee simultaneously that the flow distribution of aviation kerosene is even in a plurality of spiral winding pipes 33, guarantee the heat transfer effect.
According to a further embodiment of the invention, the first legs 31 of the plurality of helically wound pipe assemblies 3 are evenly spaced and the second legs 32 of the plurality of helically wound pipe assemblies 3 are evenly spaced.
According to a further embodiment of the present invention, the plurality of helically wound tubes 33 in each helically wound tube assembly 3 are evenly spaced.
It can be understood that, the distance between the plurality of first branch pipes 31, the distance between the plurality of second branch pipes 32, and the distance between the plurality of spirally wound pipes 33 are determined according to actual conditions, so that the spirally wound pipe assemblies 3 can be uniformly arranged to ensure that the plurality of spirally wound pipe assemblies 3 are reasonable in structure, avoid space interference, improve the compactness of the spirally wound pipes 33 and increase the heat exchange amount, thereby increasing the heat exchange amount per unit mass of the spirally wound pipe air-oil heat exchanger 1000.
According to a further embodiment of the invention, the first annular manifold 1 is located at the outer end of the first branch 31 of the plurality of spirally wound tube assemblies 3; the second annular main pipe 2 is located at one end, close to the outside, of the second branch pipes 32 of the spiral wound pipe assemblies 3, the structure is reasonable, and the annular space inside the aircraft engine can be reasonably utilized.
While embodiments of the invention have been shown and described, it will be understood by those of ordinary skill in the art that: various changes, modifications, substitutions and alterations can be made to the embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the claims and their equivalents.
Claims (10)
1. The utility model provides a spiral winding pipe air-oil heat exchanger suitable for aeroengine which characterized in that includes:
the first annular main pipe is provided with an oil inlet;
the second annular main pipe is provided with an oil outlet, the second annular main pipe and the first annular main pipe are coaxially arranged in a spaced manner in the front-rear direction, and the second annular main pipe is positioned in front of the first annular main pipe;
the spiral winding pipe assemblies are arranged in a spiral winding mode to form a cylindrical shape and are communicated between the first annular main pipe and the second annular main pipe in parallel, so that aviation kerosene flows through the spiral winding pipe assemblies respectively after entering the first annular main pipe from the oil inlet, then flows through the spiral winding pipe assemblies and is gathered in the second annular main pipe, is discharged from the oil outlet and finally enters the combustion chamber for combustion, and high-temperature and high-pressure air is cooled by the forward and backward transverse sweeping of the spiral winding pipe assemblies after being cooled.
2. The helically wound tube air-oil heat exchanger suitable for use in an aircraft engine of claim 1, wherein the oil inlet is one or more; one or more oil outlets are arranged.
3. The helically wound tube air-oil heat exchanger adapted for use in an aircraft engine of claim 1, wherein the helically wound tube assembly is made of an alloy material.
4. The helically wound tube air-oil heat exchanger suitable for use in an aircraft engine of claim 1, wherein each helically wound tube assembly comprises a first leg, a second leg, and a plurality of helically wound tubes, the first leg extending in a radial direction and being in communication with the first annular manifold; the second branch pipe extends in a radial direction and communicates with the second annular manifold; one ends of the spiral winding pipes are respectively paved in a row in the radial direction and are respectively communicated with the first branch pipes, and the other ends of the spiral winding pipes are respectively paved in a row in the radial direction and are respectively communicated with the second branch pipes.
5. The helically wound tube air-oil heat exchanger suitable for use in an aircraft engine of claim 4, wherein the first branch tube communicates with the first annular manifold via a first connecting tube, and the second branch tube communicates with the second annular manifold via a second connecting tube.
6. The air-oil heat exchanger with spirally wound tubes suitable for use in an aircraft engine of claim 5, wherein the first connecting tube and the second connecting tube are both porous flat tubes.
7. The air-oil heat exchanger with the spirally-wound pipes suitable for the aircraft engine according to claim 6, wherein the porous flat pipes comprise a plurality of pipe holes which are independent from each other and parallel, and the direction of flow of the aviation kerosene in the plurality of pipe holes of the same porous flat pipe is consistent.
8. The helically wound tube air-oil heat exchanger adapted for use in an aircraft engine of claim 4, wherein the first legs of the plurality of helically wound tube assemblies are evenly spaced and the second legs of the plurality of helically wound tube assemblies are evenly spaced.
9. The helically wound tube air-oil heat exchanger adapted for use in an aircraft engine of claim 4, wherein the plurality of helically wound tubes in each helically wound tube assembly are evenly spaced.
10. The helically wound tube air-to-oil heat exchanger adapted for use in an aircraft engine of claim 4, wherein the first annular manifold is located at an outer end of the first leg of the plurality of helically wound tube assemblies; the second annular manifold is located at an outer end of the second legs of the plurality of spiral wound coil assemblies.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110008180.8A CN112833685A (en) | 2021-01-05 | 2021-01-05 | Spiral winding pipe air-oil heat exchanger suitable for aeroengine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110008180.8A CN112833685A (en) | 2021-01-05 | 2021-01-05 | Spiral winding pipe air-oil heat exchanger suitable for aeroengine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112833685A true CN112833685A (en) | 2021-05-25 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110008180.8A Pending CN112833685A (en) | 2021-01-05 | 2021-01-05 | Spiral winding pipe air-oil heat exchanger suitable for aeroengine |
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| CN (1) | CN112833685A (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101705870A (en) * | 2009-12-03 | 2010-05-12 | 北京航空航天大学 | Air-oil heat exchanger suitable for gas turbine engine |
| CN103486877A (en) * | 2013-09-23 | 2014-01-01 | 上海交通大学 | Flow path changing microchannel flat pipe winding type heat exchanger |
| CN106323041A (en) * | 2015-06-30 | 2017-01-11 | 杭州三花家电热管理***有限公司 | Micro-channel heat exchanger |
| CN107192279A (en) * | 2017-05-31 | 2017-09-22 | 西安交通大学 | A kind of circular passage inside spin shell and tube gas-gas heat exchanger |
| CN110553519A (en) * | 2019-09-19 | 2019-12-10 | 北京航空航天大学 | Tube bundle type heat exchanger |
-
2021
- 2021-01-05 CN CN202110008180.8A patent/CN112833685A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101705870A (en) * | 2009-12-03 | 2010-05-12 | 北京航空航天大学 | Air-oil heat exchanger suitable for gas turbine engine |
| CN103486877A (en) * | 2013-09-23 | 2014-01-01 | 上海交通大学 | Flow path changing microchannel flat pipe winding type heat exchanger |
| CN106323041A (en) * | 2015-06-30 | 2017-01-11 | 杭州三花家电热管理***有限公司 | Micro-channel heat exchanger |
| CN107192279A (en) * | 2017-05-31 | 2017-09-22 | 西安交通大学 | A kind of circular passage inside spin shell and tube gas-gas heat exchanger |
| CN110553519A (en) * | 2019-09-19 | 2019-12-10 | 北京航空航天大学 | Tube bundle type heat exchanger |
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Application publication date: 20210525 |
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