CN117346561A - Efficient annular radiator and heat exchange method - Google Patents
Efficient annular radiator and heat exchange method Download PDFInfo
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- CN117346561A CN117346561A CN202311173085.9A CN202311173085A CN117346561A CN 117346561 A CN117346561 A CN 117346561A CN 202311173085 A CN202311173085 A CN 202311173085A CN 117346561 A CN117346561 A CN 117346561A
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- 238000000034 method Methods 0.000 title claims abstract description 18
- 230000017525 heat dissipation Effects 0.000 claims abstract description 48
- 238000001816 cooling Methods 0.000 claims abstract description 19
- 238000007789 sealing Methods 0.000 claims description 12
- 238000005192 partition Methods 0.000 claims description 11
- 229910000838 Al alloy Inorganic materials 0.000 claims description 2
- 229910001069 Ti alloy Inorganic materials 0.000 claims description 2
- 229910045601 alloy Inorganic materials 0.000 claims description 2
- 239000000956 alloy Substances 0.000 claims description 2
- 239000010935 stainless steel Substances 0.000 claims description 2
- 229910001220 stainless steel Inorganic materials 0.000 claims description 2
- 230000007704 transition Effects 0.000 claims description 2
- 235000017166 Bambusa arundinacea Nutrition 0.000 claims 3
- 235000017491 Bambusa tulda Nutrition 0.000 claims 3
- 241001330002 Bambuseae Species 0.000 claims 3
- 235000015334 Phyllostachys viridis Nutrition 0.000 claims 3
- 239000011425 bamboo Substances 0.000 claims 3
- 238000009434 installation Methods 0.000 claims 1
- 230000007613 environmental effect Effects 0.000 abstract description 2
- 238000005057 refrigeration Methods 0.000 abstract 1
- 238000003466 welding Methods 0.000 description 15
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 description 8
- 239000007789 gas Substances 0.000 description 5
- 229910052786 argon Inorganic materials 0.000 description 4
- 238000010586 diagram Methods 0.000 description 2
- 239000012530 fluid Substances 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 238000006467 substitution reaction Methods 0.000 description 2
- 230000004075 alteration Effects 0.000 description 1
- 238000005219 brazing Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000003032 molecular docking Methods 0.000 description 1
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
- F28D7/00—Heat-exchange apparatus having stationary tubular conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall
- F28D7/16—Heat-exchange apparatus having stationary tubular conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall the conduits being arranged in parallel spaced relation
- F28D7/163—Heat-exchange apparatus having stationary tubular conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall the conduits being arranged in parallel spaced relation with conduit assemblies having a particular shape, e.g. square or annular; with assemblies of conduits having different geometrical features; with multiple groups of conduits connected in series or parallel and arranged inside common casing
- F28D7/1669—Heat-exchange apparatus having stationary tubular conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall the conduits being arranged in parallel spaced relation with conduit assemblies having a particular shape, e.g. square or annular; with assemblies of conduits having different geometrical features; with multiple groups of conduits connected in series or parallel and arranged inside common casing the conduit assemblies having an annular shape; the conduits being assembled around a central distribution tube
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/08—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
- B64D33/10—Radiator arrangement
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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
- F28F3/00—Plate-like or laminated elements; Assemblies of plate-like or laminated elements
- F28F3/02—Elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with recesses, with corrugations
- F28F3/04—Elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with recesses, with corrugations the means being integral with the element
- F28F3/042—Elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with recesses, with corrugations the means being integral with the element in the form of local deformations of the element
- F28F3/046—Elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with recesses, with corrugations the means being integral with the element in the form of local deformations of the element the deformations being linear, e.g. corrugations
-
- 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
- F28D2021/0021—Other heat exchangers for particular applications; Heat exchange systems not otherwise provided for for aircrafts or cosmonautics
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- General Engineering & Computer Science (AREA)
- Geometry (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Aviation & Aerospace Engineering (AREA)
- Heat-Exchange Devices With Radiators And Conduit Assemblies (AREA)
Abstract
The invention discloses a high-efficiency annular radiator and a heat exchange method. The annular radiator is used as a part of the air inlet wall surface of the aircraft engine and is used as a heat transfer surface of a heat exchanger, and a large amount of cold air is punched outside the aircraft to take away heat from high-temperature air from the engine compressor, so that the purpose of cooling the high-temperature air is achieved. The invention embeds the high-temperature resistant, high-efficient and compact plate-fin type heat dissipation core at the hot air inlet and outlet of the annular heat dissipation core, forms a parallel or serial double-heat dissipation annular heat dissipation radiator with the annular heat dissipation core, and introduces triple-cooling air into the annular heat dissipation core to exchange heat with the plate-fin type heat dissipation core, thereby improving the heat exchange efficiency of the annular heat dissipation core on the premise of not increasing the size and the weight of the annular heat dissipation core, meeting the refrigeration requirements of a high-power and ultra-high-speed aircraft engine environmental control and thermal management system, and improving the compactness of an engine system.
Description
Technical Field
The invention relates to a high-efficiency heat exchange method and a high-efficiency double-heat-dissipation annular radiator, and belongs to the field of design of aviation aircraft environmental control and thermal management systems.
Background
With the increase of the high-power demand of the engine caused by the development of the ultra-high speed of the aircraft, the requirements on the compactness and the high efficiency of the annular radiator on the environment control and the thermal management system of the aircraft are higher and higher, the requirements on the high power and the ultra-high speed of the annular radiator are difficult to meet on the premise of not increasing the size and the weight of the annular radiator, the weight and the size of the environment control and the thermal management system of the aircraft are increased by increasing the size and the weight of the annular radiator so as to improve the heat exchange capacity, the compactness is reduced, the requirements on the modern high-power and ultra-high-speed aircraft engine cannot be met, and a solution is needed.
Disclosure of Invention
Considering the continuous increase of heat exchange requirements caused by the continuous increase of the power of the aircraft engine, the weight and the space size of the aircraft must be strictly controlled at the same time, and a great contradiction exists between the weight and the space size. Based on the contradiction, the invention aims to provide the efficient annular radiator and the heat exchange method, which can improve the heat exchange efficiency of the radiator and meet the increasingly large high-power and ultrahigh-speed heat exchange requirements of the aircraft engine on the premise of not increasing the volume and the weight of the radiator.
In order to achieve the above purpose, the present invention adopts the following scheme:
a high-efficiency heat exchange method comprises the following steps,
establishing a first annular body and a second annular body which are coaxial to form a heat exchange space, wherein the diameter of the inner ring of the second annular body is larger than or equal to that of the outer ring of the first annular body;
splitting ram air from an aircraft engine inlet into three parts, namely one cold air, two cold air and three cold air, and then carrying out heat exchange on the one cold air, the two cold air and the three cold air with hot air from an aircraft engine compressor respectively, wherein:
the hot air flows in the space between the outer ring and the inner ring of the first torus;
the cold air flows in a space channel formed by the inner ring of the first annular body and forms a cross-flow type heat exchange combination with the hot air flowing between the outer ring and the inner ring of the first annular body or a cross-flow type heat exchange combination with a counter-flow type heat exchange combination with the hot air flowing between the outer ring and the inner ring of the first annular body;
the secondary cooling air flows in the space between the outer ring and the inner ring of the second torus and forms countercurrent heat exchange or concurrent heat exchange with the hot air flowing between the outer ring and the inner ring of the first torus;
the three-cooling air flows along the radial direction of the first annular body and forms cross-flow heat exchange with the hot air flowing between the outer ring and the inner ring of the first annular body.
Further, the secondary cooling air and the tertiary cooling air are formed by splitting the primary cooling air at the inner ring of the first ring body, and the heat exchange efficiency is changed by adjusting the flow ratio of the secondary cooling air and the tertiary cooling air in the primary cooling air.
Further, the heat exchange between the three cold air and the hot air is realized through a first radiator, the heat exchange between the first cold air, the second cold air and the hot air is realized through a second radiator, and the first radiator and the second radiator are two radiators with different structures.
An efficient annular radiator is arranged at the transition section of an aircraft air inlet and an engine and comprises,
the annular heat dissipation core assembly comprises a bottom cylinder, the bottom cylinder is cylindrical, the inner cylindrical surface of the bottom cylinder forms a part of an air inlet channel of an airplane, a hot edge annular flow channel is covered on the outer cylindrical surface of the bottom cylinder, the hot edge annular flow channel is a plurality of annular flow channels which are coaxial with the bottom cylinder, have the same diameter and are sequentially arranged along the axis direction of the bottom cylinder, the outer annular surface of the hot edge annular flow channel is covered with a cold edge annular flow channel, the cold edge annular flow channel is a plurality of annular flow channels which are coaxial with the bottom cylinder, have the same diameter and are sequentially arranged along the axis direction of the bottom cylinder, and the inlet of the cold edge annular flow channel is communicated with a channel formed on the cylindrical surface of the bottom cylinder;
the hot pipe nozzle comprises an inlet hot pipe nozzle and an outlet hot pipe nozzle, and the inlet hot pipe nozzle and the outlet hot pipe nozzle are respectively communicated with the hot edge annular flow passage;
the plate-fin type heat dissipation core assembly comprises a hot side direct current channel and a cold side direct current channel which are perpendicular to each other, the plate-fin type heat dissipation core assembly is arranged on the outer cylindrical surface of the bottom cylinder and is arranged between the inlet hot nozzle and the outlet hot nozzle, the inlet and the outlet of the hot side direct current channel of the plate-fin type heat dissipation core assembly are communicated with the hot side annular flow channel of the annular heat dissipation core assembly, and the cold side direct current channel of the plate-fin type heat dissipation core assembly is communicated with a channel formed by the inner cylindrical surface of the bottom cylinder.
Further, the method comprises the steps of,
the hot edge annular flow passage is formed by a hot edge corrugated plate, and the same corrugation in the hot edge corrugated plate forms a hot edge annular flow passage;
the cold edge annular flow passage is formed by a cold edge corrugated plate, and the same corrugation in the cold edge corrugated plate forms a cold edge annular flow passage.
Further, the annular heat sink core assembly further comprises,
the gas collecting hood is respectively communicated with the outlet of the inlet hot nozzle and the inlet of the outlet hot nozzle, hot air at the outlet of the inlet hot nozzle is split into two parts in the gas collecting hood, one part enters the hot side annular flow passage for heat exchange, the other part enters the hot side direct flow passage for heat exchange, and the hot air after heat exchange from the hot side direct flow passage and the hot air after heat exchange from the hot side annular flow passage are collected to the gas collecting hood and then enter the inlet of the outlet hot nozzle;
the front plate is arranged at the junction of the cold edge direct flow channel outlet of the plate-fin type heat dissipation core assembly and the cold edge annular flow channel outlet of the annular heat dissipation core assembly, and comprises a cavity capable of containing air flow and an air flow outlet;
the rear disc is arranged on the bottom cylinder, a plurality of partition boards are arranged on the rear disc, a channel communicated with the hot edge annular flow channel is formed between the adjacent partition boards, a diversion notch is formed in each partition board, and extends along the direction from the inner cylindrical surface to the outer cylindrical surface of the bottom cylinder, so that the cold edge annular flow channel is communicated with an air inlet channel part of an airplane formed by the inner cylindrical surface of the bottom cylinder.
Further, the plate-fin heat dissipation core assembly comprises cold side fins, hot side fins, cold side sealing strips, hot side sealing strips, a partition plate and side plates, wherein the cold side fins form cold side direct current channels, the hot side fins form hot side direct current channels, and the partition plate is used as a heat exchange interface of the cold side direct current channels and the hot side direct current channels.
Further, the efficient annular radiator further comprises a front support assembly, the front support assembly is connected to one axial end face of the bottom barrel, the front support assembly mainly comprises a Z-shaped ring, box-shaped pieces and a mounting ring, the Z-shaped ring is coaxially sleeved on the outer side of the outer cylindrical surface of the bottom barrel, the box-shaped pieces are distributed on the circumferential side surface of the Z-shaped ring at intervals, and the mounting ring is connected to the axial end face of the Z-shaped ring and is connected with the annular radiating core assembly.
Further, the efficient annular radiator further comprises a rear support assembly, the rear support assembly mainly comprises an L-shaped ring, a sealing ring assembly, corner blocks and a large clamping plate, the L-shaped ring is coaxially sleeved on the outer side of the mounting ring, the sealing ring assembly is arranged on one axial end face of the L-shaped ring, the corner blocks are arranged on the other axial end face of the L-shaped ring, and the large clamping plate and the small clamping plate are distributed on the side surface of the circumference direction of the L-shaped ring at intervals and are clamped with the sealing ring assembly.
Alternatively, the hot side annular flow passage and the cold side annular flow passage in the annular heat dissipation core assembly, and the hot side direct flow passage and the cold side direct flow passage in the plate-fin heat dissipation core assembly are made of stainless steel, high-temperature alloy, titanium alloy or aluminum alloy.
Compared with the prior art, the annular radiator is based on the annular radiator, and the high-efficiency compact high-temperature-resistant plate-fin heat exchanger core is designed between the inlet and the outlet of hot air to be connected in parallel (or connected in series) with the annular heat dissipation core to form double-flow-path heat exchange cooling, so that the heat exchange performance is improved by 5% -10% on the premise of not increasing the size and the weight.
Drawings
FIG. 1 is a schematic view of a high efficiency annular heat sink according to the present invention;
FIG. 2 is a front view of FIG. 1;
FIG. 3 is a top view of FIG. 1;
FIG. 4 is a left side view of FIG. 1;
FIG. 5 is a schematic diagram of a heat exchange method of the high-efficiency annular radiator of the present invention;
FIG. 6 is a schematic view of an annular heat sink core assembly;
FIG. 7 is a schematic diagram of a plate-fin heat dissipation core assembly;
FIG. 8 is a schematic view of the front bracket assembly;
FIG. 9 is a schematic view of the rear bracket assembly;
in the figure: 1-annular heat sink core assembly, 2-plate fin heat sink core assembly, 3-front bracket assembly, 4-rear bracket assembly, 11-cold edge corrugated plate, 12-hot edge corrugated plate, 13-bottom cylinder, 14-gas collecting hood, 15-hot nozzle, 16-front plate, 17-rear plate, 21-cold edge fin, 22-hot edge fin, 23-cold edge seal, 24-hot edge seal, 25-separator, 26-side plate, 31-Z-shaped ring, 32-box, 33-mounting ring, 34-rivet, 41-L-shaped ring, 42-seal ring assembly, 43-corner block, 44-size clip plate.
Detailed Description
The present invention will be further described with reference to the drawings and the specific embodiments, but it should not be construed that the scope of the subject matter of the present invention is limited to the following embodiments, and various modifications, substitutions and alterations made according to the ordinary skill and familiar means of the art to which this invention pertains are included within the scope of the present invention without departing from the above technical idea of the invention.
As shown in fig. 5, the working principle of the efficient heat exchange method of the annular radiator is as follows: the high-efficiency annular radiator is arranged in an air inlet of an aircraft and is used as a part of the air inlet, a cold source is inlet ram air, a heat source is hot air from an engine, and heat exchange of three streams is finally formed, and the high-efficiency annular radiator specifically comprises:
the first main flow path exchanges heat: a cold air in the inner cylindrical surface of the bottom cylinder 13 exchanges heat with hot air in the corrugated channel formed by the hot edge corrugated plate 12 in a cross-flow, counter-flow or concurrent flow manner so as to reduce the temperature of the hot air;
the second stream exchanges heat: part of the second cold air in the corrugated channel formed by the cold edge corrugated plate 11 and part of the hot air in the corrugated channel formed by the hot edge corrugated plate 12 flow in countercurrent or concurrent flow on the contact wall surface of the two to exchange heat so as to reduce the temperature of the hot air;
and (3) heat exchange of a third flow: the cross flow heat exchange of part of the second cold air and part of the hot air in the plate-fin heat dissipation core assembly 2 is carried out so as to reduce the temperature of the hot air;
the high-efficiency annular radiator forms three flowing heat exchange forms of two hot fluid flows (two flows are split into two at the heat pipe nozzle 15, one flow enters the hot side annular flow passage of the annular heat dissipation core assembly 1, and the other flow enters the hot side direct flow passage of the plate-fin heat dissipation core assembly 2), three cold fluid flows (one cold air, two cold air and three cold air, wherein the two cold air is split from the one cold air on the bottom cylinder 13 and enters the cold side annular flow passage, and the three cold air is split from the one cold air on the bottom cylinder 13 and enters the cold side direct flow passage in correspondence to the plate-fin heat dissipation core assembly 2).
As shown in fig. 1 to 4 and fig. 6 to 9, the annular radiator in the present embodiment includes an annular heat-dissipating core assembly 1, a plate-fin heat-dissipating core assembly 2, a front bracket assembly 3 and a rear bracket assembly 4, and the above components are coupled into a whole by using a process method such as spot welding resistance welding, argon arc welding, riveting, etc.
As shown in fig. 6, the annular heat dissipation core assembly 1 is an annular heat dissipation core formed by components such as a cold edge corrugated plate 11, a hot edge corrugated plate 12, a bottom cylinder 13, a gas collecting hood 14, a heat pipe nozzle 15, a front disk 16, a rear disk 17 and the like, and the components are connected into a whole by adopting a process method such as roll welding resistance welding, spot welding resistance welding, argon arc welding and the like. Specifically, based on the cylindrical bottom cylinder 13, a circle of hot edge corrugated plates 12 are wrapped on the outer cylindrical surface of the bottom cylinder 13 to form a plurality of coaxial hot edge annular flow passages (between adjacent wave troughs), and then a circle of cold edge corrugated plates 11 are wrapped outside the hot edge corrugated plates 12 to form a plurality of coaxial cold edge annular flow passages (between adjacent wave troughs). The gas-collecting hood 14 is communicated with the hot-edge annular flow channel, and two heat pipe nozzles 15 are arranged on the gas-collecting hood 14, and the air inlet, the flow distribution, the collection and the exhaust of hot air are realized through the gas-collecting hood 14. The nature of the gas-collecting hood 14 is that the hot air is split and collected, so that the inside of the gas-collecting hood 14 is also divided into two cavity parts, wherein one cavity is positioned at the junction of the inlet of the hot nozzle 15, the inlet of the hot-edge annular flow passage and the inlet of the hot-edge direct flow passage, and the main function is to split the air flow; the other cavity is positioned at the junction of the outlet of the hot nozzle 15, the outlet of the hot edge annular flow passage and the outlet of the hot edge direct flow passage, and is mainly used for collecting air flow. The heat exchanged secondary and tertiary air is merged in the area of the front plate 16, and the merged air flows out from the square mouth of the front plate 16 (uppermost end of fig. 5). The secondary cooling air enters the annular heat dissipation core assembly 1 and is further split into two air streams at the rear disc 17, and the two air streams enter cold edge annular flow channels (the lowest end in fig. 5) on two sides of the rear disc 17 respectively, and serve as secondary cooling air inlets and serve as secondary cooling air splitting functions. The rear plate 17 may be constructed by using a plurality of partitions arranged at intervals, the interval spaces between adjacent partitions forming a part of the hot-side annular flow passage, and the partitions themselves perforated to form a passage through which cold air enters and is split into two cold air, thereby avoiding interference with hot air.
As shown in fig. 7, the plate-fin heat dissipation core assembly 2 is composed of cold edge fins 21, hot edge fins 22, cold edge seal bars 23, hot edge seal bars 24, partition plates 25, side plates 26 and other parts, and the parts are welded into a whole by vacuum brazing. The structure of the plate fin heat dissipation core assembly 2 is identical to that of the conventional plate fin heat sink, and thus, a detailed description thereof will be omitted. When the plate-fin heat-dissipating core assembly 2 is connected with the annular heat-dissipating core assembly 1, a section of cylindrical surface of the bottom cylinder 13 can be cut, the cut cylindrical surface is replaced by the plate-fin heat-dissipating core assembly 2, and the hot-side straight-flow channel inlet and the hot-side straight-flow channel outlet of the plate-fin heat-dissipating core assembly 2 are respectively communicated with the hot-side annular flow channel in the annular heat-dissipating core assembly 1.
As shown in fig. 8, the front bracket assembly 3 is mainly used as a connecting component of the efficient annular radiator and the mounting frame on the machine, and the connecting mode is generally fixed by screw connection. The front bracket component 3 consists of Z-shaped ring 31, box-shaped piece 32, mounting ring 33, rivet 34 and other components, and the components are connected into a whole by adopting the technical methods of spot welding resistance welding, riveting, argon arc welding and the like. Specifically, the Z-shaped ring 31 belongs to a part in the front bracket assembly 3, the section of the Z-shaped ring is similar to a capital "Z" letter, and screw holes are designed on the Z-shaped ring 31, so that the connection and fixation effect of the front bracket assembly 3 can be realized. The box-shaped part 32 is formed by splicing a plurality of plates to form a box body structure, and the box-shaped part 32 is riveted on the Z-shaped ring 31 through rivets 34 and is used for improving the rigidity and the strength of the Z-shaped ring 31 during operation. The mounting ring 33 belongs to a connecting part in the front bracket assembly 3, is in a circular ring shape, is connected with the end face of the Z-shaped ring 31 on one hand, is used for connecting the annular heat dissipation core assembly 1 on the other hand, is in a resistance welding mode, and is used for realizing that the annular heat dissipation core assembly 1 is mounted on the front bracket assembly 3.
As shown in fig. 9, the rear bracket assembly 4 is generally fastened to the front bracket assembly 3 by screw connection or rivet connection for flexible docking of the rear end of the annular radiator with the front end of the engine and functions to prevent leakage of a cold air flowing through the inner wall of the annular radiator. The rear bracket assembly 4 consists of an L-shaped ring 41, a sealing ring assembly 42, an angle block 43, a large clamping plate 44 and other parts, and the parts are connected into a whole by adopting the technical methods of spot welding resistance welding, argon arc welding, riveting and the like. Specifically, the L-shaped ring 41 is a central part for assembling the corner block 43, the size clamping plate 44 and the sealing ring assembly 42, the cross section of the central part is similar to the uppercase English letter "L", and the corner block 43 and the size clamping plate 44 are riveted and fixed on the L-shaped ring 41. The seal ring assembly 42 is snap-fitted to the L-shaped ring 41 by a large and small snap-fit plate 44. The size clamp 44 is used to clamp the seal ring assembly 42. The corner block 43 allows the distance between the rear bracket assembly 4 and the front bracket assembly 3 to be adjusted by limiting the size of the corner block 43 when the rear bracket assembly 4 is assembled to the front bracket assembly 3.
The foregoing is merely one embodiment of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions easily conceivable by those skilled in the art within the technical scope of the present application should be covered in the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the foregoing claims.
Claims (10)
1. A high-efficiency heat exchange method is characterized in that: comprising the steps of (a) a step of,
establishing a first annular body and a second annular body which are coaxial to form a heat exchange space, wherein the diameter of the inner ring of the second annular body is larger than or equal to that of the outer ring of the first annular body;
splitting ram air from an aircraft engine inlet into three parts, namely one cold air, two cold air and three cold air, and then carrying out heat exchange on the one cold air, the two cold air and the three cold air with hot air from an aircraft engine compressor respectively, wherein:
the hot air flows in the space between the outer ring and the inner ring of the first torus;
the cold air flows in a space channel formed by the inner ring of the first annular body and forms a cross-flow type heat exchange combination with the hot air flowing between the outer ring and the inner ring of the first annular body or a cross-flow type heat exchange combination with a counter-flow type heat exchange combination with the hot air flowing between the outer ring and the inner ring of the first annular body;
the secondary cooling air flows in the space between the outer ring and the inner ring of the second torus and forms countercurrent heat exchange or concurrent heat exchange with the hot air flowing between the outer ring and the inner ring of the first torus;
the three-cooling air flows along the radial direction of the first annular body and forms cross-flow heat exchange with the hot air flowing between the outer ring and the inner ring of the first annular body.
2. A high efficiency heat exchange method according to claim 1, wherein: the second cold air and the third cold air are formed by shunting the first cold air at the inner ring of the first ring body, and the heat exchange efficiency is changed by adjusting the flow ratio of the second cold air and the third cold air in the first cold air.
3. A high efficiency heat exchange method according to claim 1, wherein: the heat exchange of the three-cooling air and the hot air is realized through a first radiator, the heat exchange of the one-cooling air, the two-cooling air and the hot air is realized through a second radiator, and the first radiator and the second radiator are two radiators with different structures.
4. The utility model provides a high-efficient annular radiator which characterized in that: is arranged at the transition section of the air inlet channel and the engine of the airplane and comprises,
the annular heat dissipation core assembly (1), the annular heat dissipation core assembly (1) comprises a bottom cylinder (13), the bottom cylinder (13) is cylindrical, the inner cylindrical surface of the bottom cylinder (13) forms a part of an aircraft air inlet channel, the outer cylindrical surface of the bottom cylinder (13) is covered with hot edge annular flow channels, the hot edge annular flow channels are a plurality of annular flow channels which are coaxial with the bottom cylinder (13) and have the same diameter and are sequentially arranged along the axial direction of the bottom cylinder (13), the outer annular surface of the hot edge annular flow channels is covered with cold edge annular flow channels, the cold edge annular flow channels are a plurality of annular flow channels which are coaxial with the bottom cylinder (13) and have the same diameter and are sequentially arranged along the axial direction of the bottom cylinder (13), and the inlets of the cold edge annular flow channels are communicated with the channels formed on the cylindrical surface of the bottom cylinder (13);
the hot pipe nozzle (15) comprises an inlet hot pipe nozzle and an outlet hot pipe nozzle, and the inlet hot pipe nozzle and the outlet hot pipe nozzle are respectively communicated with the hot edge annular flow passage;
the plate-fin type heat dissipation core assembly (2), the plate-fin type heat dissipation core assembly (2) comprises a hot side direct current channel and a cold side direct current channel which are perpendicular to each other, the plate-fin type heat dissipation core assembly (2) is arranged on the outer cylindrical surface of the bottom cylinder (13) and between the inlet hot nozzle and the outlet hot nozzle, the inlet and the outlet of the hot side direct current channel of the plate-fin type heat dissipation core assembly (2) are communicated with the hot side annular flow channel of the annular heat dissipation core assembly (1), and the cold side direct current channel of the plate-fin type heat dissipation core assembly (2) is communicated with the channel formed by the inner cylindrical surface of the bottom cylinder (13).
5. A high efficiency annular heat sink as defined in claim 4 wherein:
the hot edge annular flow passage is formed by a hot edge corrugated plate (12), and the same corrugation in the hot edge corrugated plate (12) forms a hot edge annular flow passage;
the cold edge annular flow passage is formed by a cold edge corrugated plate (11), and the same corrugation in the cold edge corrugated plate (11) forms a cold edge annular flow passage.
6. A high efficiency annular heat sink as defined in claim 4 wherein: the annular heat dissipation core assembly (1) further comprises,
the gas collecting hood (14) is respectively communicated with the outlet of the inlet hot nozzle and the inlet of the outlet hot nozzle, hot air at the outlet of the inlet hot nozzle is split into two parts in the gas collecting hood (14), one part enters the hot side annular flow passage for heat exchange, the other part enters the hot side direct flow passage for heat exchange, and hot air after heat exchange from the hot side direct flow passage and hot air after heat exchange from the hot side annular flow passage are converged to the gas collecting hood (14) and then enter the inlet of the outlet hot nozzle;
the front disc (16) is arranged at the junction of the cold-edge straight flow passage outlet of the plate-fin heat dissipation core assembly (2) and the cold-edge annular flow passage outlet of the annular heat dissipation core assembly (1), and the front disc (16) comprises a cavity capable of containing air flow and an air flow outlet;
the rear disc (17), rear disc (17) sets up on a section of thick bamboo (13), has the polylith baffle on rear disc (17), has formed the passageway with hot limit annular runner intercommunication between the adjacent baffle, opens on every baffle has the reposition of redundant personnel notch, and the reposition of redundant personnel notch extends along from the interior cylinder to the outer cylinder direction of a section of thick bamboo (13) for the aircraft intake duct part intercommunication that cold limit annular runner and the interior cylinder of a section of thick bamboo (13) constitute.
7. A high efficiency annular heat sink as defined in claim 4 wherein: the plate-fin heat dissipation core assembly (2) comprises cold edge fins (21), hot edge fins (22), cold edge sealing strips (23), hot edge sealing strips (24), a partition plate (25) and side plates (26), wherein the cold edge fins (21) form cold edge direct current channels, the hot edge fins (22) form hot edge direct current channels, and the partition plate (25) is used as a heat exchange interface of the cold edge direct current channels and the hot edge direct current channels.
8. A high efficiency annular heat sink as defined in claim 4 wherein: the novel heat dissipation device comprises a bottom cylinder (13), and is characterized by further comprising a front support assembly (3), wherein the front support assembly (3) is connected to one axial end face of the bottom cylinder (13), the front support assembly (3) mainly comprises a Z-shaped ring (31), box-shaped pieces (32) and a mounting ring (33), the Z-shaped ring (31) is coaxially sleeved on the outer side of the outer cylindrical surface of the bottom cylinder (13), the box-shaped pieces (32) are distributed on the circumferential side surface of the Z-shaped ring (31) at intervals, and the mounting ring (33) is connected to the axial end face of the Z-shaped ring (31) and is connected with an annular heat dissipation core assembly (1).
9. A high efficiency annular heat sink as defined in claim 8 wherein: still include back support subassembly (4), back support subassembly (4) mainly comprises L shape circle (41), sealing washer subassembly (42), corner block (43) and size cardboard (44), and L shape circle (41) cup joints in the installation circle (33) outside coaxially, and sealing washer subassembly (42) set up on one axial terminal surface of L shape circle (41), and corner block (43) set up on another axial terminal surface of L shape circle (41), and size cardboard (44) interval distribution is on the side surface of L shape circle (41) circumferencial direction and with sealing washer subassembly (42) joint.
10. A high efficiency annular heat sink as defined in claim 4 wherein: the hot side annular flow passage and the cold side annular flow passage in the annular heat dissipation core assembly (1) and the hot side direct flow passage and the cold side direct flow passage in the plate-fin heat dissipation core assembly (2) are made of stainless steel, high-temperature alloy, titanium alloy or aluminum alloy.
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| CN202311173085.9A CN117346561B (en) | 2023-09-12 | 2023-09-12 | Efficient annular radiator and heat exchange method |
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| CN202311173085.9A CN117346561B (en) | 2023-09-12 | 2023-09-12 | Efficient annular radiator and heat exchange method |
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|---|---|---|---|---|
| GB620674A (en) * | 1946-03-12 | 1949-03-29 | Bristol Aeroplane Co Ltd | Improvements in or relating to heat-exchangers |
| US5143151A (en) * | 1988-10-12 | 1992-09-01 | Heat Transfer Pty. Ltd. | End manifold for a heat exchanger |
| CN1624307A (en) * | 2004-01-13 | 2005-06-08 | 斯奈克玛马达公司 | Cooling system for high-temperature unit of aircraft engine and aircraft engine mounted with the system |
| US20190234690A1 (en) * | 2018-02-01 | 2019-08-01 | Hamilton Sundstrand Corporation | Heat exchanger |
| CN112197625A (en) * | 2020-09-30 | 2021-01-08 | 中国航空发动机研究院 | Central air intake heat exchanger for high-speed air-breathing engine |
| CN116242172A (en) * | 2022-09-08 | 2023-06-09 | 北京航空航天大学 | Low-resistance plate-fin heat exchange structure suitable for high-speed airflow |
-
2023
- 2023-09-12 CN CN202311173085.9A patent/CN117346561B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB620674A (en) * | 1946-03-12 | 1949-03-29 | Bristol Aeroplane Co Ltd | Improvements in or relating to heat-exchangers |
| US5143151A (en) * | 1988-10-12 | 1992-09-01 | Heat Transfer Pty. Ltd. | End manifold for a heat exchanger |
| CN1624307A (en) * | 2004-01-13 | 2005-06-08 | 斯奈克玛马达公司 | Cooling system for high-temperature unit of aircraft engine and aircraft engine mounted with the system |
| US20190234690A1 (en) * | 2018-02-01 | 2019-08-01 | Hamilton Sundstrand Corporation | Heat exchanger |
| CN112197625A (en) * | 2020-09-30 | 2021-01-08 | 中国航空发动机研究院 | Central air intake heat exchanger for high-speed air-breathing engine |
| CN116242172A (en) * | 2022-09-08 | 2023-06-09 | 北京航空航天大学 | Low-resistance plate-fin heat exchange structure suitable for high-speed airflow |
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| CN117346561B (en) | 2024-04-19 |
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