CN115597419A - Precooler for aircraft engine - Google Patents
Precooler for aircraft engine Download PDFInfo
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- CN115597419A CN115597419A CN202211612205.6A CN202211612205A CN115597419A CN 115597419 A CN115597419 A CN 115597419A CN 202211612205 A CN202211612205 A CN 202211612205A CN 115597419 A CN115597419 A CN 115597419A
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- 230000000712 assembly Effects 0.000 claims abstract description 26
- 238000000429 assembly Methods 0.000 claims abstract description 26
- 238000001816 cooling Methods 0.000 claims description 51
- 238000009826 distribution Methods 0.000 claims description 20
- 238000009423 ventilation Methods 0.000 claims description 7
- 238000003466 welding Methods 0.000 abstract description 15
- 238000012423 maintenance Methods 0.000 abstract description 7
- 238000000034 method Methods 0.000 description 13
- 238000005192 partition Methods 0.000 description 12
- 230000001976 improved effect Effects 0.000 description 10
- 230000008569 process Effects 0.000 description 10
- 239000000110 cooling liquid Substances 0.000 description 8
- 239000007788 liquid Substances 0.000 description 7
- 238000012546 transfer Methods 0.000 description 6
- 239000002826 coolant Substances 0.000 description 5
- 238000004519 manufacturing process Methods 0.000 description 5
- 230000008646 thermal stress Effects 0.000 description 5
- 230000017525 heat dissipation Effects 0.000 description 4
- 230000009471 action Effects 0.000 description 3
- 230000008859 change Effects 0.000 description 3
- 238000013461 design Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- 238000010791 quenching Methods 0.000 description 3
- 238000010276 construction Methods 0.000 description 2
- 238000005336 cracking Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000000171 quenching effect Effects 0.000 description 2
- 230000033228 biological regulation Effects 0.000 description 1
- 238000005520 cutting process Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 230000004044 response Effects 0.000 description 1
- 230000002441 reversible effect Effects 0.000 description 1
- 238000010408 sweeping Methods 0.000 description 1
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Classifications
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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
- F28D21/00—Heat-exchange apparatus not covered by any of the groups F28D1/00 - F28D20/00
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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
- F02C7/141—Cooling of plants of fluids in the plant, e.g. lubricant or fuel of working fluid
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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
- F28F9/262—Arrangements for connecting different sections of heat-exchange elements, e.g. of radiators for radiators
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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
- F28D21/00—Heat-exchange apparatus not covered by any of the groups F28D1/00 - F28D20/00
- F28D2021/0019—Other heat exchangers for particular applications; Heat exchange systems not otherwise provided for
- F28D2021/004—Other heat exchangers for particular applications; Heat exchange systems not otherwise provided for for engine or machine cooling systems
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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 application provides a precooler for an aircraft engine, which comprises two circular ring-shaped header components and a plurality of heat exchange assemblies, wherein each heat exchange assembly comprises a first mounting plate and a second mounting plate; the first mounting plate and the second mounting plate are both provided with hollow cavities, a plurality of micro-tubes are connected between the first mounting plate and the second mounting plate, and two ends of each micro-tube are respectively communicated with the hollow cavities on the first mounting plate and the second mounting plate; wherein gaps for air circulation are formed among the micro-pipes; wherein a plurality of heat exchange assemblies are assembled between the two header parts, and the first mounting plate and the second mounting plate of each heat exchange assembly after assembly intersect the two header parts; wherein, each header part is provided with a plurality of working medium flowing holes communicated with the hollow cavity of each heat exchange assembly. The precooler provided by the invention simultaneously solves the problems of flow-induced vibration of the heat exchange tube, high welding and assembling difficulty of the heat exchange assembly, high maintenance cost and the like.
Description
Technical Field
The application relates to the field of aircraft engine cooling equipment, in particular to a precooler for an aircraft engine.
Background
The hypersonic strong precooling engine can be used as a power system of an aerospace vehicle which can be horizontally taken off and landed and reused, can realize starting from the Mach number 0 and high-performance navigation within the Mach number range of 0-6, and is a novel power device which is very important in the aerospace technical field. Relevant data show that when the aircraft flies at Mach 5, the temperature of airflow entering the engine after deceleration can reach over 1000 ℃, the high air inlet temperature not only causes the performance of engine materials to be poor and the reliability to be reduced, but also causes the air compressibility to be reduced, the performance of a power system to be rapidly reduced, and the thrust requirement of the aerospace aircraft is difficult to meet. One of the existing solutions is to reduce the temperature of the air flow by installing a precooler in the air inlet, so as to improve the working environment of the engine and meet the power performance of the aircraft at high mach number.
Most of the existing precooler structures are micro-fine tube bundle type heat exchangers, and high-temperature air is used for transversely sweeping a large number of micro-fine tube bundles to exchange heat with a cooling working medium flowing in the micro-fine tubes. Compared with the traditional tube bundle heat exchanger, the micro-tube bundle heat exchanger has higher compactness and better heat exchange capacity, but has the following new problems:
1. the micro-fine pipe is long, so that strong flow-induced vibration is easily generated, and a heat transfer pipe is damaged in serious cases, so that the heat exchange performance and the operation safety of the precooler are influenced;
2. the microtubes usually change along the length direction of the tube according to a certain curvature, and are limited by the requirement of extremely high compactness of the precooler, the mounting precision of tens of thousands of microtubes in the welding process is difficult to ensure, and the welding assembly difficulty is high;
3. the structure of the cooling liquid side or the air side of the traditional precooler is designed in an integrated mode, when the heat exchange assembly is damaged, the whole precooler needs to be replaced, and the maintenance cost is high.
Disclosure of Invention
Aiming at the problems, the invention provides a precooler for an aircraft engine, which solves the problems of flow-induced vibration of a heat exchange tube, high welding and assembling difficulty of the heat exchange assembly, high maintenance cost and the like by modularly assembling the heat exchange assembly into a precooler main body.
The technical scheme of the invention is as follows:
a precooler for an aircraft engine comprises two annular header components and a plurality of heat exchange assemblies, wherein each heat exchange assembly comprises a first mounting plate and a second mounting plate;
the first mounting plate and the second mounting plate are both provided with hollow cavities, a plurality of micro-tubes are connected between the first mounting plate and the second mounting plate, and two ends of each micro-tube are respectively communicated with the hollow cavities on the first mounting plate and the second mounting plate; wherein gaps for air to flow from outside to inside are formed among the micro-tubes;
wherein a plurality of the heat exchange assemblies are assembled between the two header parts, and the first mounting plate and the second mounting plate of each of the assembled heat exchange assemblies intersect the two header parts;
and each header part is provided with a plurality of working medium flowing holes communicated with the hollow cavity of each heat exchange assembly, and cooling working media flow into the hollow cavities through the working medium flowing holes and flow into the micro-fine tubes through the hollow cavities so as to cool air circulating in the gaps.
Optionally, a flow dividing pipe is arranged on one of the header parts, and a collecting pipe is arranged on the other header part;
a plurality of shunt holes communicated with the hollow cavity on the first mounting plate are formed in the shunt pipe;
the collecting pipe is provided with a plurality of collecting holes communicated with the hollow cavity on the second mounting plate;
the cooling working medium flows into the hollow cavity on the first mounting plate from the plurality of flow distribution holes, flows into the microtubes through the corresponding hollow cavities, flows into the hollow cavity on the second mounting plate from the microtubes, and flows out of the hollow cavity through the plurality of flow collecting holes.
Optionally, the shunt tube and the collecting tube are respectively arranged on the inner ring edge or the outer ring edge of the corresponding header part.
Optionally, a flow dividing pipe and a flow collecting pipe are arranged on each of the two header parts;
a first shunt pipe and a first collecting pipe are arranged on one collecting pipe part, the first shunt pipe is provided with a plurality of shunt holes communicated with the hollow cavity on the first mounting plate, and the first collecting pipe is provided with a plurality of collecting holes communicated with the hollow cavity on the first mounting plate;
a second shunt pipe and a second collecting pipe are arranged on the other collecting pipe part; the second flow distribution pipe is provided with a plurality of flow distribution holes communicated with the hollow cavity on the second mounting plate, and the second flow collection pipe is provided with a plurality of flow collection holes communicated with the hollow cavity on the second mounting plate;
each hollow cavity is divided into a plurality of first areas and a plurality of second areas; wherein,
the first flow dividing pipe, the second flow dividing pipe and the corresponding micro-pipes in the first area form a first cooling channel;
the second flow dividing pipe, the first flow collecting pipe and the corresponding micro-fine pipe in the second area form a second cooling channel;
the flow directions of the cooling working mediums in the first cooling channel and the second cooling channel are opposite.
Optionally, the first shunt pipe and the second shunt pipe are both arranged on the inner ring edge of the corresponding header part, and the first header pipe and the second header pipe are both arranged on the outer ring edge of the corresponding header part; or,
the first flow dividing pipe and the second flow dividing pipe are arranged on the corresponding inner ring edge of the header part, and the second flow dividing pipe and the first flow dividing pipe are arranged on the corresponding outer ring edge of the header part.
Optionally, a plurality of U-shaped flow distribution plates are disposed in the hollow cavity, and the U-shaped flow distribution plates are staggered between two sides of the hollow cavity, so as to divide the microtubes in the hollow cavity into the microtubes in the first area and the microtubes in the second area.
Optionally, the cross sections of the shunt tube and the collecting tube are in a segmental shape.
Optionally, at least one partition is coupled between the first mounting plate and the second mounting plate, the partition being spaced between the plurality of microtubes.
Optionally, a plurality of ventilation holes are distributed on the partition plate.
Compared with the prior art, the method has the following advantages:
the invention provides a precooler for an aircraft engine, which comprises two annular header components and a plurality of heat exchange assemblies, wherein each heat exchange assembly comprises a first mounting plate and a second mounting plate; the first mounting plate and the second mounting plate are both provided with hollow cavities, a plurality of micro-tubes are connected between the first mounting plate and the second mounting plate, and two ends of each micro-tube are respectively communicated with the hollow cavities on the first mounting plate and the second mounting plate; wherein gaps for air to flow from outside to inside are formed among the micro-pipes; wherein a plurality of heat exchange assemblies are assembled between two header parts, and the first mounting plate and the second mounting plate of each heat exchange assembly after assembly intersect with the two header parts; wherein, each collecting pipe part is provided with a plurality of working medium flowing holes communicated with the hollow cavity of each heat exchange assembly, and cooling working medium flows into the hollow cavity through the working medium flowing holes and flows into the microtubes through the hollow cavity so as to cool air circulating in the gaps.
Through adopting the technical scheme of this application, two mounting panels and well cavity body form heat exchange assemblies's major structure, assemble a plurality of heat exchange assemblies and form the modular precooler on the ring shape header part, have the following several at least and show the progress:
1. in the embodiment of the invention, the lengths of the microtubes arranged on the two mounting plates on each heat exchange assembly are shorter, the rigidity of the short tubes is better, the flow-induced vibration strength caused by transverse air outside the tube bundle is greatly weakened, and a better anti-vibration effect can be obtained without adding an additional support structure;
2. the structure of the heat exchange assembly in the embodiment of the invention can be matched with the micro straight tube, and the micro straight tube is directly welded on the two mounting plates, so that the strength and the safety of the welding position are improved, and the welding and assembling process is simpler and more convenient;
3. the plurality of heat exchange assemblies in the embodiment of the invention are mutually independent and cooperate, air simultaneously enters the plurality of heat exchange assemblies for enhanced heat exchange, when the precooler is damaged, only the damaged heat exchange assembly needs to be replaced, and the maintenance cost is low;
4. in the embodiment of the invention, a plurality of heat exchange assemblies are arranged in the circumferential direction and welded to form a sleeve-shaped heat exchange structure, the micro-tubes on each heat exchange assembly are laid between two mounting plates in the circumferential direction, and are integrally abutted end to form a plurality of annular micro-tube layers arranged from the inner wall of the sleeve to the outer wall of the sleeve, so that the compactness of the micro-tubes is higher, the contact area of the micro-tubes and air is increased, and the integral heat exchange capacity is obviously improved;
5. when a plurality of heat exchange assemblies are assembled between two circular-ring-shaped header pipe components, the casing-shaped heat exchange structure with the microtubes as the pipe wall surfaces can be integrally formed only by changing the assembling direction of the heat exchange assemblies, so that the omnibearing cooling of air entering from the periphery of the pipe wall is ensured, the microtubes are welded only according to the vertical distance between two mounting plates, the concentricity between the microtubes in the plurality of heat exchange assemblies is not required to be maintained during welding, and the welding and assembling difficulty is greatly reduced;
6. the plurality of heat exchange assemblies in the embodiment of the invention are connected with the header part, the flow distribution of the local cooling working medium can be regulated and controlled by changing the parameters of each heat exchange assembly, the flexibility is higher, and the uniformity of the integral heat exchange is improved.
Drawings
In order to more clearly illustrate the technical solutions of the present application, the drawings required to be used in the description of the present application will be briefly described below, and it is apparent that the drawings in the following description are only some embodiments of the present application, and it is obvious for those skilled in the art that other drawings may be obtained according to these drawings without inventive labor.
Fig. 1 is a schematic overall structural view of a precooler for an aircraft engine according to an embodiment of the application;
FIG. 2 is a schematic view, in partial configuration, of a precooler for an aircraft engine according to yet another embodiment of the present application;
fig. 3 is a schematic structural diagram of a heat exchange assembly according to still another embodiment of the present application.
Description of reference numerals:
1. a header part; 2. a heat exchange assembly; 3. a microtube; 4. a hollow cavity; 41. a first cavity; 42. a second cavity; 5. a shunt tube; 51. a shunt hole; 6. a header pipe; 61. a manifold hole; 7. a liquid inlet; 8. a liquid outlet; 9. a partition plate; 91. a ventilation hole; 10. a through hole; 11. a first mounting plate; 12. a second mounting plate; 13. a U-shaped splitter plate; 14. and (7) installing holes.
Detailed Description
The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are some, but not all, embodiments of the present application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.
In the related art, the heat exchange capacity of the heat exchange tube adopted by the tube bundle type heat exchanger with the conventional size is limited, and the strong precooling requirement under the high Mach number condition is difficult to meet. The micro-fine tube 3-beam precooler has high compactness and heat exchange capacity, and can complete high-efficiency heat exchange with incoming high-temperature air in a very short time. Therefore, the micro-tube 3-beam precooler is a main precooler used for an aerospace vehicle and ensuring the normal operation of an aircraft engine. In view of the problems in the background art, it can be seen that the micro-tube 3-bundle precooler in the prior art meets the requirements of the engine precooler for compactness and heat exchange capability, but new problems arise, such as: the problems of thermal stress caused by uneven temperature distribution in the quenching process, vibration caused by air passing through the heat transfer pipe, large welding assembly of the micro-pipe 3 bundles, high maintenance cost and the like.
At present, in order to solve some problems of a micro-tube 3-beam precooler in the market, researchers provide a precooler which is radially offset and arranged, the plurality of heat exchange assemblies 2 are coaxially sleeved step by step, the difficulty of manufacturing and assembling is reduced to a certain extent, in the actual manufacturing and assembling process, the concentricity with the same height needs to be ensured among the micro-tubes 3 in each layer of the heat exchange assemblies 2, the assembling difficulty can be increased by welding the radial laminated structures step by step, the engineering realization difficulty is high, and the improved effect is not obvious. In addition, no relevant solution exists for other problems of the micro-tube 3-beam precooler, and further development of the aircraft engine precooler is in the blank stage.
In view of this, the embodiment of the present application provides a precooler for an aircraft engine, and the heat exchange assembly 2 is assembled into a modular precooler body in a limited space, and the straight-tube type microtubes 3 with shorter lengths can be installed on the modular heat exchange assembly 2 by using the characteristics of easy manufacturing, assembly and disassembly of the modularization, so as to provide a design scheme for the aircraft engine precooler, which has the advantages of high compactness, strong heat exchange capability, low manufacturing and assembly difficulty, low maintenance cost, resistance to flow induced vibration and the like.
Referring to fig. 1-2, fig. 1 is a schematic diagram illustrating the overall structure of a precooler of an aircraft engine according to the invention; fig. 2 is a schematic view of a part of the structure of the precooler for an aircraft engine shown in the present invention. The design scheme of the invention is as follows:
a precooler for an aircraft engine comprises two annular header parts 1 and a plurality of heat exchange assemblies 2, wherein each heat exchange assembly 2 comprises a first mounting plate 11 and a second mounting plate 12;
the first mounting plate 11 and the second mounting plate 12 are both provided with hollow cavities 4, a plurality of micro-tubes 3 are connected between the first mounting plate 11 and the second mounting plate 12, and two ends of each micro-tube 3 are respectively communicated with the hollow cavities 4 on the first mounting plate 11 and the second mounting plate 12; wherein, gaps for air to flow from outside to inside are formed among the micro-tubes 3;
wherein a plurality of heat exchange assemblies 2 are assembled between two header parts 1, and a first mounting plate 11 and a second mounting plate 12 of each of the assembled heat exchange assemblies 2 intersect with the two header parts 1;
wherein, each header part 1 is provided with a plurality of working medium flowing holes communicated with the hollow cavity 4 of each heat exchange assembly 2, and a cooling working medium flows into the hollow cavity 4 through the working medium flowing holes and flows into the microtubes 3 through the hollow cavity 4 so as to cool air circulating in gaps.
Specifically, by fitting a plurality of heat exchange modules 2 between two annular header members 1, the plurality of heat exchange modules 2 abut against each other, that is, a double pipe-shaped heat exchange structure is formed with the heat exchange modules 2 as a circular pipe wall surface. As shown in fig. 1, white arrows indicate the direction of air flow, air flows from the outer wall surface of the pipe to the inner wall surface of the pipe, and cooled air flows out from the annular opening and finally enters the aircraft engine. The assembly of the precooler and the engine is the same as that of the conventional precooler, and the invention is not repeated. Each heat exchange assembly 2 has two mounting plates and two hollow cavities 4, for example, a single heat exchange assembly 2 is used, the first mounting plate 11 and the first cavity 41 are integrally formed, the second mounting plate 12 and the second cavity 42 are integrally formed, and the microtube 3 communicates the first cavity 41 and the second cavity 42, so that the cooling working medium flows from the first cavity 41 to the second cavity 42 after flowing through the microtube 3, or flows from the second cavity 42 to the first cavity 41 after flowing through the microtube 3, or flows from the first cavity 41 and the second cavity 42 to the second cavity 42 and the first cavity 41 which are opposite to each other after flowing through the microtube 3.
As shown in fig. 1, two header members 1 are, from front to rear, a front header member and a rear header member, the annular opening of the front header member communicating with the engine. The first mounting plate 11 intersects the two header members 1 such that both ends of the first mounting plate 11 are welded to the front header member and the rear header member, and the second mounting plate 12 intersects the two header members 1 such that both ends of the second mounting plate 12 are welded to the front header member and the rear header member. Specifically, the first mounting plate 11 and the second mounting plate 12 are perpendicular to the radial direction of the header pipe member 1, the plurality of micro-tubes 3 between the first mounting plate 11 and the second mounting plate 12 are nearly parallel to the circumferential direction of the header pipe member 1 to form a plurality of annular micro-tube layers stacked in the radial direction of the header pipe member 1, the micro-tubes 3 are more compact, the contact area of the micro-tubes 3 with the air is increased, and the overall heat exchange capacity is significantly improved.
The first mounting plate 11 and the second mounting plate 12 are mirror-symmetrical, and the microtubes 3 are vertically connected to the two opposite mounting plates to form a rectangular heat dissipation assembly. Taking the first mounting plate 11 as an example, the first mounting plate 11 has a rectangular plate-like structure, and the length is the same as the distance between the two header parts 1, so that the first mounting plate 11 is fixed to the two header parts 1; the height is the same as the distance between the outer and inner rings of the header assembly 1, so that the first mounting plate 11 has an optimal compactness of the microtubes 3 on the plate surface formed by the length and height thereof within a limited mounting space. The first mounting plate 11 is provided with a plurality of mounting holes 14, and the microtubes 3 are welded to the first mounting plate 11 through the mounting holes 14 and communicate with the first cavity 41. The first cavity 41 is a rectangular cavity and is welded to the first mounting plate 11, and the first cavity 41 is opened with a through hole 10, the through hole 10 is communicated with the working medium flow holes on the header part 1, so that the cooling working medium in the header part 1 flows into the plurality of first cavities 41 through the plurality of working medium flow holes respectively.
In the embodiment, because a plurality of heat exchange assemblies 2 are modularly assembled to form the precooler main body, and the distance between the first mounting plate 11 and the second mounting plate 12 is equal to the length of the microtubes 3, the required microtubes 3 are shorter, and the problem of flow-induced vibration caused by the overlong length of the microtubes 3 in the traditional structure is solved; because the length of the microtube 3 is shorter, the microtube 3 is welded on the two mounting plates in a straight line along the length direction of the tube, and the mounting precision is higher; the mounting holes 14 can be arranged along the length direction and the height direction of the mounting plate, so that a micro tube layer is formed along the length direction, a plurality of micro tube layers are formed along the height direction, the compactness among the micro tube layers is higher than that of a traditional micro tube 3-beam precooler, the concentricity among all the layers is not required to be kept, and meanwhile, the welding difficulty is greatly reduced; the plurality of heat exchange assemblies 2 simultaneously flow into the cooling working medium, so that the overall flow distribution of the precooler is more uniform. The invention realizes that the heat exchange component 2 with strong heat exchange capability, high reliability and low engineering realization difficulty is assembled into the precooler main body in a modularized way, and provides a design scheme with good heat exchange performance, strong vibration resistance, low maintenance cost and low manufacturing and assembling difficulty for the aircraft engine precooler.
In a specific implementation, a flow dividing pipe 5 is arranged on one header part 1, and a flow collecting pipe 6 is arranged on the other header part 1;
a plurality of shunt holes 51 communicated with the hollow cavity 4 on the first mounting plate 11 are arranged on the shunt pipe 5;
a plurality of collecting holes 61 communicated with the hollow cavity 4 on the second mounting plate 12 are formed in the collecting pipe 6;
wherein, the cooling working medium flows into the hollow cavity 4 on the first mounting plate 11 from the plurality of flow dividing holes 51, flows into the microtubes 3 through the corresponding hollow cavities 4, flows into the hollow cavity 4 on the second mounting plate 12 from the microtubes 3, and flows out of the hollow cavity 4 through the plurality of collecting holes 61.
Specifically, a margin of several millimeters is left at the inlet and outlet of the heat exchange assembly 2 for welding with the header part 1 through each shunt hole 51 and the header hole 61; the manifold 6 and the shunt tubes 5 are welded to cover the corresponding shunt holes 51 and the manifold holes 61 to form a complete cooling medium flow path. In the cooling working medium flow path, a liquid inlet 7 is arranged on the front end face of a shunt pipe 5 of a front header pipe part 1 and used for introducing a cooling working medium into the shunt pipe 5, a plurality of shunt holes 51 communicated with first cavities 41 are arranged on the rear end face of the shunt pipe 5 and used for shunting the cooling working medium to flow to the plurality of first cavities 41, a plurality of flow collecting holes 61 communicated with second cavities 42 are arranged on the front end face of a header pipe 6 of a rear header pipe part 1, and a liquid outlet 8 is arranged on the rear end face and used for enabling the cooling working medium after heat exchange to flow out of the second cavities 42, so that the cooling working medium is introduced from the front header pipe part 1, sequentially passes through the first cavities 41, the microtubes 3 and the second cavities 42 and flows out of the rear header pipe part 1.
In a possible embodiment, the flow dividing tubes 5 and the flow collecting tubes 6 are arranged on the inner or outer annular edge of the corresponding header part 1, respectively. In this embodiment, the cooling medium has a plurality of flow paths. When the shunt tubes 5 are positioned on the inner ring edge of the front header component 1 and the shell of the header 6 is positioned on the inner ring edge of the rear header component 1, the through holes 10 of the first cavity 41 and the through holes 10 of the second cavity 42 are positioned on the diagonal line of the bottom surface of the rectangular heat dissipation assembly; when the shunt tube 5 is positioned on the inner ring edge of the front header component 1 and the shell of the header 6 is positioned on the outer ring edge of the rear header component 1, the through hole 10 of the first cavity 41 and the through hole 10 of the second cavity 42 are positioned on the space diagonal line of the rectangular heat dissipation assembly; when the shunt tubes 5 are positioned on the outer ring edge of the front header component 1 and the shell of the header 6 is positioned on the outer ring edge of the rear header component 1, the through holes 10 of the first cavity 41 and the through holes 10 of the second cavity 42 are positioned on the diagonal line of the top surface of the rectangular radiating assembly; when the shunt tubes 5 are located on the outer ring edge of the front header part 1 and the header 6 shell is located on the inner ring edge of the rear header part 1, the through holes 10 of the first cavity 41 and the through holes 10 of the second cavity 42 are located on the diagonal of the space of the rectangular heat dissipation assembly.
The through holes 10 of the first cavity 41 correspond to the flow dividing holes 51 one by one, and the through holes 10 of the second cavity 42 correspond to the collecting holes 61 one by one. Of course, the positions of the shunt tubes 5 of the front header member 1 and the positions of the flow tubes 6 of the rear header member 1 may be interchanged, so that the cooling medium flows from the first cavity 41 to the second cavity 42 after flowing through the microtubes 3, or flows from the second cavity 42 to the first cavity 41 after flowing through the microtubes 3. Therefore, the modular construction and modular assembly mode of the embodiment of the invention enables the low-temperature working medium flow distribution of the precooler to the internal heat exchange assembly 2 to be more uniform, and meanwhile, the flow path of the cooling working medium can be selected from a plurality of forms, thereby realizing the regulation and control of the working medium flow distribution at local positions and further improving the uniformity of the whole heat exchange. Compared with the existing precooler, the water-cooled type water-cooled precooler has more advantages in the aspects of heat exchange, vibration resistance and construction and assembly.
In the related art, the precooler at high mach numbers is required to quench the high temperature air by at least 1000 ℃ within a response time of tens of milliseconds. In the quenching process, the temperature uniformity among the micro-fine tubes 3 is poor, so that a great temperature gradient exists among the micro-fine tubes 3 along the air flowing direction, the thermal stress change caused by the temperature gradient change in the precooler is caused by the adjustment of the flight state, the metal material is subjected to thermal fatigue damage, the potential risks such as welding crack of a micro heat transfer tube exist, and the navigation safety of the aerospace aircraft is even influenced. As shown in fig. 3, fig. 3 is a schematic structural diagram of the heat exchange assembly. The application provides a preferable technical scheme that:
the two header parts 1 are provided with a flow dividing pipe 5 and a header pipe 6;
a first shunt pipe and a first collecting pipe are arranged on one collecting pipe part 1, the first shunt pipe is provided with a plurality of shunt holes 51 communicated with the hollow cavity 4 on the first mounting plate 11, and the first collecting pipe is provided with a plurality of collecting holes 61 communicated with the hollow cavity 4 on the first mounting plate 11;
the other header part 1 is provided with a second shunt pipe and a second header pipe; the second flow dividing pipe is provided with a plurality of flow dividing holes 51 communicated with the hollow cavity 4 on the second mounting plate 12, and the second flow dividing pipe is provided with a plurality of collecting holes 61 communicated with the hollow cavity 4 on the second mounting plate 12;
each hollow cavity 4 is divided into a plurality of first regions and a plurality of second regions; wherein,
the first flow dividing pipe, the second flow dividing pipe and the corresponding microtubes 3 in the first area form a first cooling channel;
the second flow dividing pipe, the first flow dividing pipe and the corresponding microtubes 3 in the second area form a second cooling channel;
the flow directions of the cooling working mediums in the first cooling channel and the second cooling channel are opposite.
Specifically, by providing the flow dividing pipes 5 and the flow collecting pipes 6 on both the front header member 1 and the rear header member 1, an alternating flow path is established in which the cooling medium flows through the microtubes 3 to the opposing second cavity 42 and first cavity 41 after flowing from the flow dividing holes 51 of both header members 1 to the first cavity 41 and second cavity 42 simultaneously. Under the staggered flow path, the heat exchanger is divided into a first cooling channel and a second cooling channel which are independent and have opposite flow directions, so that the countercurrent heat exchange in adjacent heat exchange area pipes in the heat exchange assembly 2 can be realized under the condition of not reducing the heat exchange capacity of the precooler, the heat exchange uniformity in a single module is improved, and the problems of welding cracking of the micro heat transfer pipes and the like caused by thermal stress are relieved.
In this embodiment, a plurality of U-shaped flow distribution plates 13 are disposed in the hollow cavity 4, and the U-shaped flow distribution plates 13 are arranged between two sides of the hollow cavity 4 in a staggered manner, so as to divide the microtubes 3 in the hollow cavity 4 into the microtubes 3 in the first area and the microtubes 3 in the second area. Two through holes 10 are arranged on the front surface of the first cavity 41 close to the front header component 1 and are respectively communicated with a flow dividing hole 51 of a first flow dividing pipe of the front header component 1 and a collecting hole 61 of the first flow dividing pipe; the second cavity 42 is provided with two through holes 10 near the rear view surface of the rear header part 1, and the through holes are respectively communicated with the branch holes 51 of the second branch pipe of the rear header part 1 and the collecting holes 61 of the second branch pipe.
In the first cooling channel, the cooling working medium flows from front to back and flows into the microtubes 3 in the first area in the first cavity 41, and because the U-shaped splitter plate 13 in the first cavity 41 blocks the cooling working medium to flow into the microtubes 3 in the second area in the first cavity 41, the cooling working medium flows into the second cavity 42 from the first area and flows through the rear header component 1. Meanwhile, in the second cooling channel, the cooling working medium flows from back to front and flows into the microtubes 3 in the second area in the second cavity 42, and because the U-shaped splitter plate 13 in the second cavity 42 blocks the cooling working medium from flowing into the microtubes 3 in the first area in the second cavity 42, the cooling working medium flows into the first cavity 41 from part of the second area and flows from the front header part 1.
The diversion holes 51 of the first diversion pipe and the diversion holes 51 of the second diversion pipe must be respectively communicated with the first cavity 41 and the second cavity 42, so that the cooling working medium is simultaneously introduced into the first cavity 41 and the second cavity 42 to realize staggered flow. Therefore, the cooling working medium forms a plurality of first areas and second areas which are adjacent to each other and flow in a staggered manner in the rectangular heat exchange assembly 2, the reverse flow of the working medium in the pipe is realized between the adjacent heat exchange areas in the assembly, the heat exchange uniformity is improved, the whole precooler works in a relatively uniform temperature field, the influence of internal thermal stress of the precooler caused by severe heat exchange is reduced, the risks of welding cracking and the like of the superfine heat transfer pipe caused by the thermal stress are reduced, and the service life and the safety of equipment are improved;
it should be noted that the opening of the U-shaped flow distribution plate 13 forms a first region toward the side of the flow distribution pipe 5 communicating with the through hole 10 of the first chamber 41, and the opening of the U-shaped flow distribution plate forms a second region toward the side of the flow collection pipe 6 communicating with the through hole 10 of the first chamber 41.
In another possible embodiment, the first shunt tubes and the second shunt tubes are both arranged on the inner ring edge of the corresponding header part 1, and the first manifold tubes and the second manifold tubes are both arranged on the outer ring edge of the corresponding header part 1; or,
the first shunt tubes and the second shunt tubes are provided on the inner ring edge of the corresponding header part 1, and the second shunt tubes and the first shunt tubes are provided on the outer ring edge of the corresponding header part 1.
Specifically, embodiments of the present invention can vary the location of the shunt tubes 5 and the shunt tubes 6 to achieve various forms of staggered flow paths. Exemplarily, when the first flow dividing pipe is located at the inner ring edge of the front header part 1, and the first flow dividing pipe is located at the outer ring edge of the front header part 1, the second flow dividing pipe is located at the inner ring edge of the rear header part 1, and the second flow dividing pipe is located at the outer ring edge of the rear header part 1, in this embodiment, the flow manner of the cooling working medium from front to back is: flows from the inner side flow dividing hole 51 of the front header member 1 to the first cavity 41, and flows through the fine tube 3 to the inner side flow dividing hole 61 of the rear header member 1 after being divided in the first cavity 41; the flow mode from back to front is as follows: flows from the outer branch flow holes 51 of the rear header member 1 to the second chamber 42, and flows through the micro-tubes 3 to the outer collecting holes 61 of the front header member 1 after being branched in the second chamber 42.
When the branch flow holes 51 are located at the inner and outer rings of the front and rear header members 1 and 1, respectively, the U-shaped branch flow plates 13 in the first and second cavities 41 and 42 should be mirror symmetric with respect to the center line of the rectangular heat exchange assembly 2.
Exemplarily, when the first branch pipe is located at the inner ring edge of the front header part 1, and the first branch pipe is located at the outer ring edge of the front header part 1, and the second branch pipe is located at the outer ring edge of the rear header part 1, and the second branch pipe is located at the inner ring edge of the rear header part 1, in this embodiment, the flow manner of the cooling working medium from front to back is: flows from the inner side flow dividing hole 51 of the front header member 1 to the first cavity 41, and flows through the fine tube 3 to the outer side flow dividing hole 61 of the rear header member 1 after being divided in the first cavity 41; the flow mode from back to front is as follows: flows from the inner branch flow holes 51 of the rear header member 1 to the second chamber 42, and flows through the micro-tubes 3 to the outer header flow holes 61 of the front header member 1 after being branched in the second chamber 42.
When the flow dividing holes 51 are located at the inner rings of the front header part 1 and the rear header part 1, respectively, the U-shaped flow dividing plates 13 in the first cavity 41 and the second cavity 42 should be polar-axisymmetric with respect to the center line of the rectangular heat exchange assembly 2.
It can be understood that the first shunt tube may be located at the outer ring edge of the front header part 1, the first header may be located at the inner ring edge of the front header part 1, and the counter-flow heat exchange in the micro-tubes 3 in the first area and the second area adjacent to each other in the heat exchange assembly 2 may be implemented by correspondingly arranging the second shunt tube and the second header.
As shown in fig. 1 to 3, it is illustrated that when the first manifold is located at the inner ring edge of the front header member 1 and the first manifold is located at the outer ring edge of the front header member 1, the second manifold is located at the outer ring edge of the rear header member 1, and the second manifold is located at the precooler at the inner ring edge of the rear header member 1.
In another possible example, the shunt tube 5 and the collector tube 6 are scalloped in cross-section. The segment is a segment of a circular pipe with a bottom plane formed by a straight cutting part. When the flow dividing pipe 5 and the flow collecting pipe 6 are welded on the edge of the inner ring and the edge of the outer ring of the circular ring component, the bottom plane is in contact with the circular ring component, and when cooling working media are continuously and greatly introduced into the pipe, the pressure-bearing capacity is higher.
In yet another example, at least one partition 9 may be coupled between the first mounting plate 11 and the second mounting plate 12, and the partition 9 may be spaced between the plurality of microtubes 3. The partition plate 9 has a supporting function, so that the rigidity of the single heat exchange assembly 2 can be increased, and the rigidity of the whole precooler is further improved. Further, a plurality of ventilation holes 91 are provided in the partition plate 9 in a dispersed manner. The ventilation holes 91 are formed in the partition plate 9, air with different temperatures on two sides of the partition plate 9 can reach the other side through the ventilation holes 91, the mixed flow effect is achieved, the temperature difference of the air on the two sides of the partition plate 9 is reduced, and the uniformity of heat exchange of the air outside the pipe is further improved.
The flow and heat transfer process will be described with reference to fig. 1-3, wherein black arrows represent the flow direction of the cooling medium, the cooling liquid enters the first shunt pipe from the liquid inlet 7 of the front header part 1, enters the second shunt pipe from the liquid inlet 7 of the rear header part 1, flows into the first shunt chamber and the second shunt chamber of each heat exchange assembly 2 after being shunted once through the shunt holes 51, and then is shunted twice through the U-shaped shunt plate 13 in the heat exchange assembly 2, the cooling liquid flows through the microtubes 3 in the first region to the second chamber 42 from front to back through the first chamber 41, and simultaneously flows through the microtubes 3 in the second region to the first chamber 41 from back to front through the second chamber 42, and as the microtubes 3 in the adjacent first region and second region are shunted by different shunt chambers on the same side, a counter-flow in the tubes between the adjacent heat exchange regions is formed, in the above process, the cooling liquid in the microtubes 3 fully exchanges heat with the high-temperature air outside the tubes, and at the same time, the ventilation holes 91 on the partition plate 9 are opened to facilitate the uniform air-exchange of the air-exchange side, so that the air-exchange holes 9 are more uniform; since the precooler is installed at the middle and rear sections of the air inlet channel, the annular opening of the rear header component 1 in fig. 1 is already blocked by other air inlet components, so that the high-temperature air outside the tubes can flow out of the precooler from the annular opening of the front header component 1 after precooling; after heat exchange, the cooling liquid in the pipe continuously flows into the hollow cavity 4 on the other side along the microtube 3, primary confluence is completed in the hollow cavity 4, then the cooling liquid flows out of the flow collecting hole 61, secondary confluence is completed in the flow collecting pipe 6, and finally the cooling liquid flows out of the cooling liquid passage from the liquid outlet 8, so that the process of cooling high-temperature air is completed.
It should be noted that, in the present specification, the embodiments are all described in a progressive manner, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments may be referred to each other.
It should also be noted that, in this document, the terms "upper", "lower", "left", "right", "inner", "outer", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of describing the present invention and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present invention. Moreover, relational terms such as "first" and "second" are used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions or neither should the relative importance be understood or implied. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or terminal that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or terminal.
The precooler for an aircraft engine provided by the present application is described in detail above, and the principles and embodiments of the present application are explained herein using specific examples, which are provided only for the purpose of assisting the understanding of the present application and should not be construed as limiting the present application. While various modifications of the illustrative embodiments and applications will be apparent to those skilled in the art based upon this disclosure, it is not necessary or necessary to exhaustively enumerate all embodiments, and all obvious variations and modifications can be resorted to, falling within the scope of the disclosure.
Claims (9)
1. A precooler for an aircraft engine comprising two annular header members and a plurality of heat exchange assemblies, each heat exchange assembly comprising a first mounting plate and a second mounting plate;
the first mounting plate and the second mounting plate are both provided with hollow cavities, a plurality of micro-tubes are connected between the first mounting plate and the second mounting plate, and two ends of each micro-tube are respectively communicated with the hollow cavities on the first mounting plate and the second mounting plate; wherein gaps for air to flow from outside to inside are formed among the micro-tubes;
wherein a plurality of the heat exchange assemblies are assembled between the two header parts, and the first mounting plate and the second mounting plate of each of the assembled heat exchange assemblies intersect the two header parts;
and each header part is provided with a plurality of working medium flowing holes communicated with the hollow cavity of each heat exchange assembly, and cooling working medium flows into the hollow cavity through the working medium flowing holes and flows into the microtubes through the hollow cavity so as to cool air circulating in the gaps.
2. A precooler for an aircraft engine as claimed in claim 1, wherein one of the header members is provided with a flow dividing tube and the other header member is provided with a flow collecting tube;
a plurality of shunt holes communicated with the hollow cavity on the first mounting plate are formed in the shunt tubes;
the collecting pipe is provided with a plurality of collecting holes communicated with the hollow cavity on the second mounting plate;
the cooling working medium flows into the hollow cavity on the first mounting plate from the plurality of flow distribution holes, flows into the microtubes through the corresponding hollow cavities, flows into the hollow cavity on the second mounting plate from the microtubes, and flows out of the hollow cavity through the plurality of flow collecting holes.
3. A precooler for an aircraft engine as claimed in claim 2,
the shunt tubes and the collecting tubes are respectively arranged on the inner ring edge or the outer ring edge of the corresponding collecting pipe component.
4. A precooler for an aircraft engine as claimed in claim 1, wherein both header members are provided with flow dividing tubes and flow collecting tubes;
a first shunt pipe and a first collecting pipe are arranged on one collecting pipe part, the first shunt pipe is provided with a plurality of shunt holes communicated with the hollow cavity on the first mounting plate, and the first collecting pipe is provided with a plurality of collecting holes communicated with the hollow cavity on the first mounting plate;
a second shunt pipe and a second shunt pipe are arranged on the other header part; the second flow distribution pipe is provided with a plurality of flow distribution holes communicated with the hollow cavity on the second mounting plate, and the second flow collection pipe is provided with a plurality of flow collection holes communicated with the hollow cavity on the second mounting plate;
each hollow cavity is divided into a plurality of first areas and a plurality of second areas; wherein,
the first flow dividing pipe, the second flow dividing pipe and the corresponding micro-fine pipes in the first area form a first cooling channel;
the second flow dividing pipe, the first flow dividing pipe and the corresponding micro-pipe in the second area form a second cooling channel;
the flow directions of the cooling working mediums in the first cooling channel and the second cooling channel are opposite.
5. A precooler for an aircraft engine as claimed in claim 4,
the first flow dividing pipe and the second flow dividing pipe are arranged on the inner ring edges of the corresponding header parts, and the first flow dividing pipe and the second flow dividing pipe are arranged on the outer ring edges of the corresponding header parts; or,
the first flow dividing pipe and the second flow dividing pipe are arranged on the corresponding inner ring edge of the header part, and the second flow dividing pipe and the first flow dividing pipe are arranged on the corresponding outer ring edge of the header part.
6. The precooler for an aircraft engine according to claim 4, wherein a plurality of U-shaped flow distribution plates are arranged in the hollow cavity, and the plurality of U-shaped flow distribution plates are arranged in a staggered manner between two sides of the hollow cavity to divide the microtubes in the hollow cavity into microtubes in a first area and microtubes in a second area.
7. A precooler for an aircraft engine as claimed in claim 2 or claim 4, wherein the cross-sections of the flow-dividing tube and the flow-collecting tube are scalloped.
8. The precooler for an aircraft engine of claim 1, wherein at least one baffle is coupled between the first mounting plate and the second mounting plate, the baffle being spaced between the plurality of microtubes.
9. A precooler for an aircraft engine as claimed in claim 8, wherein a plurality of ventilation holes are dispersed in the baffle.
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| CN202211612205.6A CN115597419B (en) | 2022-12-15 | 2022-12-15 | Precooler for aircraft engine |
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Cited By (1)
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| CN115597419B (en) | 2023-03-28 |
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