CN112197625B - Central air intake heat exchanger for high-speed air-breathing engine - Google Patents
Central air intake heat exchanger for high-speed air-breathing engine Download PDFInfo
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- CN112197625B CN112197625B CN202011059125.3A CN202011059125A CN112197625B CN 112197625 B CN112197625 B CN 112197625B CN 202011059125 A CN202011059125 A CN 202011059125A CN 112197625 B CN112197625 B CN 112197625B
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- heat exchanger
- core
- air
- core body
- heat exchange
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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
- F28D9/00—Heat-exchange apparatus having stationary plate-like or laminated conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall
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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
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
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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
- F28F27/00—Control arrangements or safety devices specially adapted for heat-exchange or heat-transfer apparatus
- F28F27/02—Control arrangements or safety devices specially adapted for heat-exchange or heat-transfer apparatus for controlling the distribution of heat-exchange media between different channels
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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
- F28F9/001—Casings in the form of plate-like arrangements; Frames enclosing a heat exchange core
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Heat-Exchange Devices With Radiators And Conduit Assemblies (AREA)
Abstract
The utility model provides a heat exchanger admits air in center for high-speed formula engine of breathing in, including heat exchanger body and heat transfer core, the heat exchanger body includes square intake duct, core installation department and gas outlet channel, square intake duct the core installation department reaches the gas outlet channel connects gradually, and is a plurality of the heat transfer core install in around the inner wall of core installation department, core installation department axial direction is equipped with the air chamber, the heat transfer core with be equipped with annular channel between the core installation department, the heat exchanger still includes mode change-over valve, mode change-over valve locates the core installation department with junction between the gas outlet channel. The precooling heat exchanger structure is designed to be suitable for a square air inlet of an existing mainstream airplane.
Description
Technical Field
The present disclosure relates to the field of pre-cooling heat exchangers for high-speed engines, and more particularly to a central intake heat exchanger for a high-speed air-breathing engine.
Background
The speeding up of aircraft has extremely important military and civilian value.
The aircraft turbine engine has the characteristics of horizontal take-off and landing, reusability and high specific impulse, so that the aircraft turbine engine is the preferred scheme of a high-speed aircraft. At present, the main scheme is to adopt inlet precooling, namely, the inlet temperature of a turbine is reduced through a precooling heat exchanger or a water spraying device, and the inlet temperature rise caused by pneumatic heating effect during high-speed flight is counteracted, so that the turbine can fly at higher speed.
The precooling system of the 'bent blade' and 'wearing blade' engines of the British RE I company is the most representative, US10,012,177B2 discloses the system arrangement of the precooling engine, the defect is that the engine system is very complicated, supercritical helium is adopted as an intermediate cycle working medium in the precooling heat exchanger, the pressure is as high as 200bar, and the harsh requirement is provided for the processing technology. Chinese patents CN109372657A, CN105275662B and CN107939528A disclose similar system configurations. The precooler of the 'bent knife' and 'worn knife' engines of British RE I company consists of 16000 thin-wall heat exchange capillary tubes, the diameter of the heat exchange capillary tubes is only 0.88mm, the wall thickness is 0.04mm, and the total length reaches 20 km; the inside is supercritical helium as a coolant, with extremely high internal pressure. The heat transfer coefficient is inversely proportional to the diameter of the channel, and the reduction of the diameter of the capillary tube makes the capillary tube have extremely strong cooling capacity, but has the disadvantage of high processing difficulty, and especially puts extremely high requirements on the welding process of the capillary tube because the pressure inside the capillary tube is high on one hand, and the wall thickness of the capillary tube is extremely small on the other hand. Densely packed capillary welds present a significant challenge to the welding technique.
Chinese invention CN107218133A discloses an efficient compact precooling heat exchanger for precooling air-breathing engines, which is in principle very close to that of uk RE I company. Only the flow direction of the internal cooling fluid is different. As previously analyzed, the difficulty and cost of manufacturing capillary tube heat exchangers has limited the development of this technology.
At present, precooling heat exchangers researched at home and abroad are mostly referred to heat exchangers with a circular ring structure similar to a 'swimming ring' of British RE I company, high-temperature gas radially passes through the heat exchangers from the outside, and an annular air inlet channel with an air inlet cone is matched with the heat exchangers. At present, the most common air inlet channel is a square air inlet channel without an air inlet cone, and no heat exchanger structure matched with the air inlet channel exists at present.
Disclosure of Invention
The present disclosure provides a central air intake heat exchanger for a high-speed air intake engine, which is designed with a precooling heat exchanger structure adapted to a square air intake passage of an existing mainstream airplane.
According to one aspect of the disclosure, the central air inlet heat exchanger for the high-speed air suction type engine comprises a heat exchanger body and a heat exchange core body, wherein the heat exchanger body comprises a square air inlet channel, a core body installation part and an air outlet channel, the square air inlet channel, the core body installation part and the air outlet channel are sequentially connected, a plurality of heat exchange core bodies are installed on the periphery of the inner wall of the core body installation part, an air chamber is arranged at the axial center of the core body installation part, an annular channel is arranged between the heat exchange core body and the core body installation part, the heat exchanger further comprises a mode conversion valve, and the mode conversion valve is arranged at the connecting position between the core body installation part and the air outlet channel;
when the engine works at a low speed, the mode conversion valve is in an open state, the heat exchange core is in short connection, and air flow directly enters the turbine engine through the square air inlet channel, the air chamber and the mode conversion valve in sequence along the axial direction;
when the engine works at a high speed, the mode conversion valve is in a closed state, air flow enters the air chamber from the square air inlet channel and then is divided into a plurality of air flows, each air flow is respectively passed through the annular channel after passing through the heat exchange core bodies, each air flow is cooled and then is collected to the air outlet channel, and finally enters the turbine engine.
According to at least one embodiment of the present disclosure, the core mounting portion is cylindrical.
According to at least one embodiment of this disclosure, the heat exchange core is "zither" shape, four the heat exchange core install in the inner wall of core installation department.
According to at least one embodiment of the present disclosure, the mode switching valve is a guide vane type valve.
According to at least one embodiment of the present disclosure, the heat exchange core is a plate-fin heat exchanger.
Drawings
The accompanying drawings, which are included to provide a further understanding of the disclosure and are incorporated in and constitute a part of this specification, illustrate exemplary embodiments of the disclosure and together with the description serve to explain the principles of the disclosure.
Fig. 1 is a schematic structural view of a heat exchanger of the present disclosure.
FIG. 2 is a schematic view of the internal structure of the heat exchanger of the present disclosure; wherein the direction of the arrow is the direction of air flow.
FIG. 3 is a schematic structural view of a heat exchanger core of the present disclosure.
FIG. 4 is a schematic view of the configuration of the mode switching valve of the present disclosure; wherein FIG. 4a is an open state; fig. 4b is the closed state.
Detailed Description
The present disclosure will be described in further detail with reference to the drawings and embodiments. It is to be understood that the specific embodiments described herein are for purposes of illustration only and are not to be construed as limitations of the present disclosure. It should be further noted that, for the convenience of description, only the portions relevant to the present disclosure are shown in the drawings.
It should be noted that the embodiments and features of the embodiments in the present disclosure may be combined with each other without conflict. The present disclosure will be described in detail below with reference to the accompanying drawings in conjunction with embodiments.
As shown in fig. 1 and fig. 2, the present disclosure discloses a central air intake heat exchanger for a high-speed air-breathing engine, which includes a heat exchanger body 1 and a heat exchange core 2, the heat exchanger body 1 includes a square air intake channel 11, a core installation part 12 and an air outlet channel 13, the square air intake channel 11, the core installation part 12 and the air outlet channel 13 are connected in sequence, a plurality of heat exchange cores 2 are installed around the inner wall of the core installation part 12, an air chamber 121 is arranged at the axial center of the core installation part 12, an annular channel 122 is arranged between the heat exchange core 2 and the core installation part 12, the heat exchanger further includes a mode switching valve 3, and the mode switching valve 3 is arranged at the joint between the core installation part 12 and the air outlet channel 13; the turbine engine nose cone 100 is provided at the outlet of the outlet channel 13.
When the engine works at a low speed (flying Ma <2), the mode conversion valve 3 is in an open state, the heat exchange core body 2 is in short circuit, and air flow directly enters the turbine engine through the square air inlet 11, the air chamber 121 and the mode conversion valve 3 in sequence along the axial direction;
when the engine works at a high speed (flying Ma >2), the mode conversion valve 3 is in a closed state, air flow enters the air chamber 121 from the square air inlet channel 11 and then is divided into a plurality of air flows, each air flow passes through the annular channel 122 and then is collected to the air outlet channel after being cooled by the plurality of heat exchange core bodies 2, and finally enters the turbine engine.
According to at least one embodiment of the present disclosure, the core mount 12 is cylindrical.
As shown in fig. 3, according to at least one embodiment of the present disclosure, the heat exchanging core 2 is in a shape of a "koto", and the heat exchanging core is installed on the inner wall of the core installation part. The heat exchange medium flows through the heat exchange core body from left to right to increase the temperature, and the air passes through the heat exchange core body from the air chamber to the annular channel to decrease the temperature. The heat exchange medium can be water, glycol, organic working medium, or various liquid metals, such as gallium-indium alloy and potassium-sodium alloy, which are required to be protected.
As shown in fig. 4, the mode switching valve 3 is a guide vane type valve according to at least one embodiment of the present disclosure, wherein fig. 4a is an open state; fig. 4b is the closed state.
According to at least one embodiment of the present disclosure, the heat exchange core 2 is a plate-fin heat exchanger.
The core body is formed by splicing four plate-fin heat exchangers, the outline view is a structure with an outer circle and an inner square, and the manufacturing is simple; the heat exchange core body is cooled by liquid, so that the heat exchange capacity is strong; the processing method of the plate-fin heat exchanger is mature, so that the processing cost and the processing difficulty are greatly reduced; the heat exchanger is connected with a conventional turbine engine, and the turbine engine can realize high-speed flight without being changed. The present disclosure is useful for speeding up military and civilian aircraft engines.
In the description herein, reference to the description of the terms "one embodiment/mode," "some embodiments/modes," "example," "specific example," or "some examples," etc., means that a particular feature, structure, material, or characteristic described in connection with the embodiment/mode or example is included in at least one embodiment/mode or example of the application. In this specification, the schematic representations of the terms used above are not necessarily intended to be the same embodiment/mode or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments/modes or examples. Furthermore, the various embodiments/aspects or examples and features of the various embodiments/aspects or examples described in this specification can be combined and combined by one skilled in the art without conflicting therewith.
It will be understood by those skilled in the art that the foregoing embodiments are provided merely for clarity of explanation and are not intended to limit the scope of the disclosure. Other variations or modifications may occur to those skilled in the art, based on the foregoing disclosure, and are still within the scope of the present disclosure.
Claims (4)
1. The central air inlet heat exchanger for the high-speed air suction type engine is characterized by comprising a heat exchanger body and a heat exchange core body, wherein the heat exchange core body is a plate-fin heat exchanger, the heat exchanger body comprises a square air inlet channel, a core body installation part and an air outlet channel, the square air inlet channel, the core body installation part and the air outlet channel are sequentially connected, a plurality of heat exchange core bodies are installed around the inner wall of the core body installation part, an air chamber is arranged at the axial center of the core body installation part, an annular channel is arranged between the heat exchange core body and the core body installation part, the heat exchanger further comprises a mode conversion valve, and the mode conversion valve is arranged at the joint between the core body installation part and the air outlet channel;
when the engine works at a low speed, the mode conversion valve is in an open state, the heat exchange core is in short connection, and air flow directly enters the turbine engine through the square air inlet channel, the air chamber and the mode conversion valve in sequence along the axial direction;
when the engine works at a high speed, the mode conversion valve is in a closed state, air flow enters the air chamber from the square air inlet channel and then is divided into a plurality of air flows, each air flow is respectively passed through the annular channel after passing through the heat exchange core bodies, each air flow is cooled and then is collected to the air outlet channel, and finally enters the turbine engine.
2. The heat exchanger of claim 1, wherein the core mount is cylindrical.
3. The heat exchanger of claim 1, wherein said heat exchanging core is "koto" shaped, and wherein said heat exchanging core is mounted to an inner wall of said core mounting portion.
4. The heat exchanger of claim 1, wherein the mode switching valve is a vane-type valve.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011059125.3A CN112197625B (en) | 2020-09-30 | 2020-09-30 | Central air intake heat exchanger for high-speed air-breathing engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011059125.3A CN112197625B (en) | 2020-09-30 | 2020-09-30 | Central air intake heat exchanger for high-speed air-breathing engine |
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| Publication Number | Publication Date |
|---|---|
| CN112197625A CN112197625A (en) | 2021-01-08 |
| CN112197625B true CN112197625B (en) | 2022-05-06 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202011059125.3A Active CN112197625B (en) | 2020-09-30 | 2020-09-30 | Central air intake heat exchanger for high-speed air-breathing engine |
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Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115597420B (en) * | 2022-12-15 | 2023-04-25 | 四川大学 | Staggered counter-flow type precooling heat exchanger |
| CN117346561B (en) * | 2023-09-12 | 2024-04-19 | 贵州永红航空机械有限责任公司 | Efficient annular radiator and heat exchange method |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6260352B1 (en) * | 1997-09-12 | 2001-07-17 | Rolls-Royce Deutschland Ltd & Co Kg | Turbofan aircraft engine |
| CN1585884A (en) * | 2001-11-09 | 2005-02-23 | 奥尔堡工业公司 | A heat exchanger, combination with heat exchanger and method of manufacturing the heat exchanger |
| CN105443247A (en) * | 2014-09-19 | 2016-03-30 | 波音公司 | Pre-cooler inlet ducts that utilize active flow-control and systems and methods including the sam |
| CN106014637A (en) * | 2016-06-07 | 2016-10-12 | 中国人民解放军国防科学技术大学 | Air precooling compression aircraft engine and hypersonic velocity aircraft |
| CN107701312A (en) * | 2017-11-10 | 2018-02-16 | 中国空气动力研究与发展中心计算空气动力研究所 | A kind of hypersonic jets |
-
2020
- 2020-09-30 CN CN202011059125.3A patent/CN112197625B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6260352B1 (en) * | 1997-09-12 | 2001-07-17 | Rolls-Royce Deutschland Ltd & Co Kg | Turbofan aircraft engine |
| CN1585884A (en) * | 2001-11-09 | 2005-02-23 | 奥尔堡工业公司 | A heat exchanger, combination with heat exchanger and method of manufacturing the heat exchanger |
| CN105443247A (en) * | 2014-09-19 | 2016-03-30 | 波音公司 | Pre-cooler inlet ducts that utilize active flow-control and systems and methods including the sam |
| CN106014637A (en) * | 2016-06-07 | 2016-10-12 | 中国人民解放军国防科学技术大学 | Air precooling compression aircraft engine and hypersonic velocity aircraft |
| CN107701312A (en) * | 2017-11-10 | 2018-02-16 | 中国空气动力研究与发展中心计算空气动力研究所 | A kind of hypersonic jets |
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| CN112197625A (en) | 2021-01-08 |
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