CN115573815B - Heat exchange device utilizing jet injection of aero-engine bleed air - Google Patents
Heat exchange device utilizing jet injection of aero-engine bleed air Download PDFInfo
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- CN115573815B CN115573815B CN202211228872.4A CN202211228872A CN115573815B CN 115573815 B CN115573815 B CN 115573815B CN 202211228872 A CN202211228872 A CN 202211228872A CN 115573815 B CN115573815 B CN 115573815B
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- bleed air
- aeroengine
- air
- heat exchanger
- bypass
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- 238000002347 injection Methods 0.000 title claims abstract description 47
- 239000007924 injection Substances 0.000 title claims abstract description 47
- 230000001105 regulatory effect Effects 0.000 claims abstract description 16
- 238000005057 refrigeration Methods 0.000 claims description 11
- 238000011144 upstream manufacturing Methods 0.000 claims description 9
- 239000007921 spray Substances 0.000 claims description 5
- 230000000694 effects Effects 0.000 description 7
- 238000001816 cooling Methods 0.000 description 6
- 239000000243 solution Substances 0.000 description 3
- 238000006467 substitution reaction Methods 0.000 description 2
- 230000001276 controlling effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000007599 discharging Methods 0.000 description 1
- 230000001939 inductive effect Effects 0.000 description 1
- 238000002156 mixing Methods 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
- 230000000087 stabilizing effect Effects 0.000 description 1
Classifications
-
- 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
-
- 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
- F02C7/16—Cooling of plants characterised by cooling medium
- F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Heat-Exchange Devices With Radiators And Conduit Assemblies (AREA)
- Control Of Turbines (AREA)
Abstract
The application belongs to the technical field of design of jet heat exchangers by utilizing bleed air jet of an aero-engine, and particularly relates to a heat exchange device by utilizing jet injection of bleed air jet of an aero-engine, which comprises the following components: the side wall of the cold edge outlet part of the heat exchanger is provided with a through hole; the outlet end of the aeroengine air entraining pipeline penetrates through the through hole and stretches into the cold edge outlet part of the heat exchanger; the annular pipe is arranged in the cold edge outlet part of the heat exchanger, and the side wall of the annular pipe is provided with an inflow hole and a plurality of jet holes; the inflow hole is communicated with the outlet end of the aeroengine bleed air pipeline; each jet hole is distributed along the circumferential direction of the annular tube and faces the cold edge outlet of the heat exchanger; the aeroengine bleed air pressure regulating valve is arranged on the aeroengine bleed air pipeline to maintain the stability of the air flow pressure in the aeroengine bleed air pipeline.
Description
Technical Field
The application belongs to the technical field of design of jet injection heat exchange devices by utilizing bleed air jet of an aero-engine, and particularly relates to a jet injection heat exchange device by utilizing bleed air jet of an aero-engine.
Background
Be provided with many heat transfer devices in the aeroengine, utilize the air to cool off the heat flow, like the smooth oil cooler in the aeroengine, in order to guarantee the flow of the cold limit air of heat transfer device, draw the high-pressure air current in the aeroengine, jet injection is carried out to the cold limit air of heat transfer device, however, aeroengine has different operating modes, under different operating modes, there is great difference in the pressure of drawing out the high-pressure air current from aeroengine, it is great to lead to the cold limit air flow of heat transfer device to change, it is undulant great to the cooling effect of heat flow, be difficult to satisfy the application demand.
The present application has been made in view of the above-described technical drawbacks.
It should be noted that the above disclosure of the background art is only for aiding in understanding the inventive concept and technical solution of the present application, which is not necessarily prior art to the present patent application, and should not be used for evaluating the novelty and creativity of the present application in the case where no clear evidence indicates that the above content has been disclosed at the filing date of the present application.
Disclosure of Invention
The application aims to provide a heat exchange device utilizing jet injection of air entraining jet of an aeroengine, so as to overcome or alleviate at least one technical defect of the known aspects.
The technical scheme of the application is as follows:
a heat exchange device utilizing jet injection of air entraining jet of an aircraft engine, comprising:
The side wall of the cold edge outlet part of the heat exchanger is provided with a through hole;
The outlet end of the aeroengine air entraining pipeline penetrates through the through hole and stretches into the cold edge outlet part of the heat exchanger;
The annular pipe is arranged in the cold edge outlet part of the heat exchanger, and the side wall of the annular pipe is provided with an inflow hole and a plurality of jet holes; the inflow hole is communicated with the outlet end of the aeroengine bleed air pipeline; each jet hole is distributed along the circumferential direction of the annular tube and faces the cold edge outlet of the heat exchanger;
The aeroengine bleed air pressure regulating valve is arranged on the aeroengine bleed air pipeline to maintain the stability of the air flow pressure in the aeroengine bleed air pipeline.
According to at least one embodiment of the application, in the heat exchange device utilizing jet injection of air entraining jet of the aeroengine, the annular pipe and the outlet part of the cold side of the heat exchanger are coaxially arranged, and the radial size of the annular pipe is 0.1-0.2 times of the radial size of the outlet part of the cold side of the heat exchanger.
According to at least one embodiment of the present application, in the heat exchange device using air-entraining jet injection of an aeroengine, the heat exchange device further includes:
A plurality of jet nozzles, each jet nozzle being disposed in a corresponding one of the jet apertures.
According to at least one embodiment of the application, in the heat exchange device utilizing jet injection of air entraining jet of the aeroengine, each jet nozzle is in a Laval nozzle configuration.
According to at least one embodiment of the present application, in the heat exchange device using air-entraining jet injection of an aeroengine, the heat exchange device further includes:
the aeroengine bleed air pressure gauge is arranged on the aeroengine bleed air pipeline and is positioned at the downstream of the aeroengine bleed air pressure regulating valve.
According to at least one embodiment of the present application, in the heat exchange device using air-entraining jet injection of an aeroengine, the heat exchange device further includes:
The aero-engine bleed air stop valve is arranged on the aero-engine bleed air pipeline and is positioned at the downstream of the aero-engine bleed air pressure regulating valve.
According to at least one embodiment of the application, in the heat exchange device utilizing aero-engine bleed air jet injection, the side wall of the inlet part of the heat exchanger is provided with a perforation;
Air entraining pipeline of aeroengine the side wall is provided with a bypass air-inducing hole, the bypass bleed hole is positioned at the upstream of the bleed pressure regulating valve of the aeroengine;
Utilize aeroengine bleed efflux to draw heat transfer device who draws, still include:
The inlet end of the bypass air-entraining pipeline is communicated with the bypass air-entraining hole, and the outlet end of the bypass air-entraining pipeline penetrates through the perforation and stretches into the cold edge inlet part of the heat exchanger;
a refrigeration turbine disposed on the bypass bleed air duct;
The bypass bleed air manometer is arranged on the air bleed pipeline of the aeroengine and is positioned at the upstream of the bypass bleed air hole;
The bypass bleed air stop valve is arranged on the bypass bleed air pipeline and is positioned at the upstream of the refrigeration turbine;
the controller is connected with the bypass bleed air pressure gauge and the bypass bleed air stop valve, and controls the bypass bleed air stop valve to be opened when the pressure signal transmitted by the bypass bleed air pressure gauge is greater than a set threshold value.
According to at least one embodiment of the application, in the heat exchange device utilizing aeroengine bleed air jet injection, the side wall of the outlet end of the bypass bleed air pipeline is provided with a plurality of jet holes; the spray holes are axially distributed along the bypass bleed air duct towards the cold side outlet of the heat exchanger.
According to at least one embodiment of the present application, in the heat exchange device using air-entraining jet injection of an aeroengine, the heat exchange device further includes:
the bypass bleed air thermometer is arranged on the bypass bleed air pipeline and is positioned at the downstream of the refrigerating turbine.
According to at least one embodiment of the present application, in the heat exchange device using air-entraining jet injection of an aeroengine, the heat exchange device further includes:
The inlet end of the cold edge outlet exhaust pipeline of the heat exchanger is in a horn shape and is communicated with the cold edge outlet of the heat exchanger.
Drawings
FIG. 1 is a schematic view of a heat exchange device utilizing jet injection of bleed air jet of an aircraft engine provided by an embodiment of the application;
wherein:
1-a heat exchanger; 2-an aeroengine bleed air duct; 3-an annular tube; 4-an aeroengine bleed air pressure regulating valve; 5-jet nozzles; 6-an aeroengine bleed air manometer; 7-an aeroengine bleed air stop valve; 8-bypass bleed air duct; 9-a refrigeration turbine; 10-bypass bleed air manometer; 11-a bypass bleed air shut-off valve; 12-a controller; 13-bypass bleed air thermometers; 14-cold side outlet exhaust duct of heat exchanger.
For the purpose of better illustrating the present embodiments, certain elements of the drawings may be omitted, enlarged or reduced and do not represent the actual product dimensions, and furthermore, the drawings are for illustrative purposes only and are not to be construed as limiting the present patent.
Detailed Description
In order to make the technical solution of the present application and its advantages more clear, the technical solution of the present application will be further and completely described in detail with reference to the accompanying drawings, it being understood that the specific embodiments described herein are only some of the embodiments of the present application, which are for explanation of the present application and not for limitation of the present application. It should be noted that, for convenience of description, only the part related to the present application is shown in the drawings, and other related parts may refer to the general design, and the embodiments of the present application and the technical features of the embodiments may be combined with each other to obtain new embodiments without conflict.
Furthermore, unless defined otherwise, technical or scientific terms used in the description of the application should be given the ordinary meaning as understood by one of ordinary skill in the art to which the application pertains. The terms "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," "outer," and the like as used in the description of the present application are merely used for indicating relative directions or positional relationships, and do not imply that the devices or elements must have a specific orientation, be constructed and operated in a specific orientation, and that the relative positional relationships may be changed when the absolute position of the object to be described is changed, thus not being construed as limiting the application. The terms "first," "second," "third," and the like, as used in the description of the present application, are used for descriptive purposes only and are not to be construed as indicating or implying any particular importance to the various components. The use of the terms "a," "an," or "the" and similar referents in the description of the application are not to be construed as limiting the amount absolutely, but rather as existence of at least one. As used in this description of the application, the terms "comprises," "comprising," or the like are intended to cover an element or article that appears before the term as such, but does not exclude other elements or articles from the list of elements or articles that appear after the term.
Furthermore, unless specifically stated and limited otherwise, the terms "mounted," "connected," and the like in the description of the present application are used in a broad sense, and for example, the connection may be a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can also be communicated with the inside of two elements, and the specific meaning of the two elements can be understood by a person skilled in the art according to specific situations.
The application is described in further detail below with reference to fig. 1.
A heat exchange device utilizing jet injection of air entraining jet of an aircraft engine, comprising:
The side wall of the cold edge outlet part of the heat exchanger 1 is provided with a through hole;
the outlet end of the aeroengine air entraining pipeline 2 passes through the through hole and stretches into the cold edge outlet part of the heat exchanger 1;
the annular pipe 3 is arranged in the cold edge outlet part of the heat exchanger 1, and the side wall of the annular pipe is provided with an inflow hole and a plurality of jet holes; the inflow hole is communicated with the outlet end of the aeroengine bleed air pipeline 2; each jet hole is circumferentially distributed along the annular tube 3 and faces the cold-side outlet of the heat exchanger 1;
the aeroengine bleed air pressure regulating valve 4 is arranged on the aeroengine bleed air pipeline 2 to maintain the stability of the air flow pressure in the aeroengine bleed air pipeline 2.
For the heat exchange device using aeroengine bleed air jet injection disclosed in the above embodiment, it can be understood by those skilled in the art that the aeroengine bleed air pipeline 2 can be connected to an aeroengine, high-pressure air flow is led out from the aeroengine, the high-pressure air flows through the aeroengine bleed air pipeline 2 and flows into the annular pipe 3, and then is injected into the cold side outlet of the heat exchanger 1 through each jet hole to jet the cold side outlet of the heat exchanger 1, so that injection of cold side air of the heat exchanger 1 is realized, and the flow rate of the cold side air of the heat exchanger 1 is ensured.
For the heat exchange device using aeroengine bleed air jet injection disclosed in the above embodiment, those skilled in the art can also understand that each jet hole is designed to be circumferentially distributed along the annular tube 3, that is, circumferentially distributed in the cold-side outlet part of the heat exchanger 1, and energy is efficiently transferred to the cold-side air of the heat exchanger 1 through boundary blending, so that the injection effect of the cold-side air of the heat exchanger 1 is enhanced, and the flow of the cold-side air of the heat exchanger 1 is ensured.
For the heat exchange device using aeroengine bleed jet injection disclosed in the above embodiment, it can be further understood by those skilled in the art that the aeroengine bleed pressure regulating valve 4 is disposed on the aeroengine bleed pipeline 2, so that the air flow pressure in the aeroengine bleed pressure regulating valve 4 can be stabilized at a desired value according to actual configuration, thereby controlling the pressure of the aeroengine for guiding high-pressure air flow, stabilizing the cold side air flow of the heat exchanger 1, and ensuring the stability of the cooling effect of the heat flow.
In some optional embodiments, in the heat exchange device using air-entraining jet injection of the aeroengine, the annular tube 3 and the cold-side outlet portion of the heat exchanger 1 are coaxially arranged, and the radial dimension of the annular tube is 0.1-0.2 times of the radial dimension of the cold-side outlet portion of the heat exchanger 1, so that the annular tube is close to the center of the cold-side outlet portion of the heat exchanger 1 and is far away from the side wall of the cold-side outlet portion of the heat exchanger 1, the injection effect of cold-side air of the heat exchanger 1 is ensured, and the flow resistance of the cold-side air of the heat exchanger 1 can be reduced.
In some alternative embodiments, in the heat exchange device using air-entraining jet injection of the aeroengine, the cross section of the annular tube 3 is streamline, and may be in particular an airfoil shape, so as to reduce the flow resistance to the cold-side air of the heat exchanger 1.
In some optional embodiments, the heat exchange device using air-entraining jet injection of the aeroengine further includes:
a plurality of jet nozzles 5, each jet nozzle 5 being disposed in a jet aperture.
In some alternative embodiments, in the heat exchange device using air-entraining jet injection of the aeroengine, each jet nozzle 5 is in a laval jet pipe configuration, that is, the radial dimension of the inlet end of each jet nozzle 5 is gradually contracted, the dimension of the outlet end of each jet nozzle 5 is gradually enlarged, high-pressure air flowing into the annular pipe 3 through the air-entraining pipeline 2 of the aeroengine can be injected into the cold-side outlet of the heat exchanger 1 through each jet nozzle 5 at a higher speed, so that the injection effect on cold-side air of the heat exchanger 1 can be improved, and the flow rate of high-pressure air drawn from the aeroengine is limited based on throttling, so that the consumption of the high-pressure air drawn from the aeroengine can be reduced.
In some optional embodiments, the heat exchange device using air-entraining jet injection of the aeroengine further includes:
The aeroengine bleed pressure gauge 6 is arranged on the aeroengine bleed pipeline 2 and is positioned downstream of the aeroengine bleed pressure regulating valve 4.
In some optional embodiments, the heat exchange device using air-entraining jet injection of the aeroengine further includes:
An aero-engine bleed air shut-off valve 7 is arranged on the aero-engine bleed air duct 2 downstream of the aero-engine bleed air pressure regulating valve 4.
In some optional embodiments, in the heat exchange device using aero-engine bleed air jet injection, the side wall of the inlet part of the heat exchanger 1 is provided with a perforation;
The side wall of the aeroengine air-entraining pipeline 2 is provided with a bypass air-entraining hole, and the bypass air-entraining hole is positioned at the upstream of the aeroengine air-entraining pressure regulating valve 4;
Utilize aeroengine bleed efflux to draw heat transfer device who draws, still include:
The inlet end of the bypass air-entraining pipeline 8 is communicated with the bypass air-entraining hole, and the outlet end of the bypass air-entraining pipeline passes through the perforation and extends into the cold edge inlet part of the heat exchanger 1;
a refrigeration turbine 9 arranged on the bypass bleed air duct 8;
The bypass bleed air manometer 10 is arranged on the air engine bleed air pipeline 2 and is positioned at the upstream of the bypass bleed air hole;
a bypass bleed air shut-off valve 11, which is arranged on the bypass bleed air duct 8 upstream of the refrigeration turbine 9;
The controller 12 is connected with the bypass bleed air pressure gauge 10 and the bypass bleed air stop valve 11, and controls the bypass bleed air stop valve 11 to be opened when the pressure signal transmitted by the bypass bleed air pressure gauge 10 is larger than a set threshold value.
As for the heat exchange device using jet injection of the bleed air jet of the aeroengine disclosed in the above embodiment, it can be understood by those skilled in the art that the bypass bleed air manometer 10 is designed to monitor the pressure of the high-pressure air flow led out from the aeroengine, when the pressure exceeds the set threshold value, the controller 12 controls the bypass bleed air stop valve 11 to open, at this time, part of the high-pressure air flow led out from the aeroengine can flow into the cold side inlet portion of the heat exchanger 1 through the bypass bleed air pipe 8, and the part of the high-pressure air flow can be cooled when flowing through the refrigeration turbine 9, and the part of the high-pressure air flow can be mixed with the air at the cold side inlet of the heat exchanger 1 in the cold side inlet portion of the heat exchanger 1, so that the cooling effect on the heat flow can be increased, that is, when the pressure of the high-pressure air flow led out from the aeroengine is too high, part of the high-pressure air flow is cooled by the refrigeration turbine 9, and the part of the high-pressure air flow can be used as part of the cold side air flow of the heat exchanger 1 for cooling the heat flow, and the part of the high-pressure air flow can be cooled by the high-efficiency cooling device 40 when flowing through the high-pressure turbine 9, and the high-pressure air flow can be cooled by the heat exchanger 1.
In some alternative embodiments, in the heat exchange device using aeroengine bleed air jet injection, the side wall of the outlet end of the bypass bleed air pipeline 8 is provided with a plurality of jet holes; the spray holes are axially distributed along the bypass air-entraining pipeline 8, and face the cold edge outlet of the heat exchanger 1, and high-pressure air flowing into the bypass air-entraining pipeline 8 can be sprayed into the cold edge inlet part of the heat exchanger 1 through the spray holes to be efficiently mixed with air in the cold edge inlet part of the heat exchanger 1, so that the cooling effect of the heat exchanger 1 is ensured.
In some optional embodiments, the heat exchange device using air-entraining jet injection of the aeroengine further includes:
a bypass bleed air thermometer 13 is arranged on the bypass bleed air duct 8 downstream of the refrigeration turbine 9.
In some optional embodiments, the heat exchange device using air-entraining jet injection of the aeroengine further includes:
the inlet end of the heat exchanger cold side outlet exhaust pipeline 14 is in a horn shape and is communicated with the cold side outlet of the heat exchanger 1 so as to be capable of discharging air flowing out of the cold side outlet of the heat exchanger 1 in an accelerating way.
In the description, each embodiment is described in a progressive manner, and each embodiment is mainly described by the differences from other embodiments, so that the same similar parts among the embodiments are mutually referred.
Having thus described the technical aspects of the present application with reference to the preferred embodiments shown in the drawings, it should be understood by those skilled in the art that the scope of the present application is not limited to the specific embodiments, and those skilled in the art may make equivalent changes or substitutions to the related technical features without departing from the principle of the present application, and those changes or substitutions will fall within the scope of the present application.
Claims (9)
1. A heat exchange device utilizing jet injection of air entraining jet of an aeroengine, comprising:
the side wall of the cold edge outlet part of the heat exchanger (1) is provided with a through hole;
the outlet end of the aeroengine air entraining pipeline (2) passes through the through hole and stretches into the cold edge outlet part of the heat exchanger (1);
The annular pipe (3) is arranged in the cold edge outlet part of the heat exchanger (1), and the side wall of the annular pipe is provided with an inflow hole and a plurality of jet holes; the inflow hole is communicated with the outlet end of the aeroengine bleed air pipeline (2); the jet holes are circumferentially distributed along the annular pipe (3) and face the cold edge outlet of the heat exchanger (1);
The aeroengine bleed air pressure regulating valve (4) is arranged on the aeroengine bleed air pipeline (2) so as to maintain the stability of the air flow pressure in the aeroengine bleed air pipeline (2);
the side wall of the inlet part of the heat exchanger (1) is provided with a perforation;
The side wall of the aeroengine air-entraining pipeline (2) is provided with a bypass air-entraining hole, and the bypass air-entraining hole is positioned at the upstream of the aeroengine air-entraining pressure regulating valve (4);
the heat exchange device utilizing jet injection of air entraining jet of the aeroengine further comprises:
a bypass bleed air pipe (8) with an inlet end communicated with the bypass bleed air hole and an outlet end extending into the cold side inlet part of the heat exchanger (1) through the perforation;
a refrigeration turbine (9) arranged on the bypass bleed air duct (8);
a bypass bleed air manometer (10) arranged on the aircraft engine bleed air duct (2) upstream of the bypass bleed air hole;
A bypass bleed air shut-off valve (11) arranged on the bypass bleed air duct (8) upstream of the refrigeration turbine (9);
The controller (12) is connected with the bypass bleed air pressure measuring meter (10) and the bypass bleed air stop valve (11), and when a pressure signal transmitted by the bypass bleed air pressure measuring meter (10) is larger than a set threshold value, the bypass bleed air stop valve (11) is controlled to be opened.
2. The heat exchange device utilizing jet injection of aeroengine bleed air as claimed in claim 1, wherein,
The annular tube (3) and the outlet part of the cold side of the heat exchanger (1) are coaxially arranged, and the radial size of the annular tube is 0.1-0.2 times of the radial size of the outlet part of the cold side of the heat exchanger (1).
3. The heat exchange device utilizing jet injection of aeroengine bleed air as claimed in claim 1, wherein,
Further comprises:
A plurality of jet nozzles (5), each jet nozzle (5) being arranged in a respective one of the jet holes.
4. A heat exchange device utilizing jet injection of aeroengine bleed air as claimed in claim 3, wherein,
Each jet nozzle (5) is in the form of a Laval nozzle.
5. The heat exchange device utilizing jet injection of aeroengine bleed air as claimed in claim 1, wherein,
Further comprises:
And the aeroengine bleed air pressure gauge (6) is arranged on the aeroengine bleed air pipeline (2) and is positioned at the downstream of the aeroengine bleed air pressure regulating valve (4).
6. The heat exchange device utilizing jet injection of aeroengine bleed air as claimed in claim 1, wherein,
Further comprises:
And the aero-engine bleed air stop valve (7) is arranged on the aero-engine bleed air pipeline (2) and is positioned at the downstream of the aero-engine bleed air pressure regulating valve (4).
7. The heat exchange device utilizing jet injection of aeroengine bleed air as claimed in claim 1, wherein,
The side wall of the outlet end of the bypass bleed air pipeline (8) is provided with a plurality of spray holes; the spray holes are axially distributed along the bypass bleed air duct (8) towards the cold side outlet of the heat exchanger (1).
8. The heat exchange device utilizing jet injection of aeroengine bleed air as claimed in claim 1, wherein,
Further comprises:
A bypass bleed air thermometer (13) is arranged on the bypass bleed air duct (8) downstream of the refrigeration turbine (9).
9. The heat exchange device utilizing jet injection of aeroengine bleed air as claimed in claim 1, wherein,
Further comprises:
and the inlet end of the cold edge outlet exhaust pipeline (14) of the heat exchanger is in a horn shape and is communicated with the cold edge outlet of the heat exchanger (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211228872.4A CN115573815B (en) | 2022-10-09 | 2022-10-09 | Heat exchange device utilizing jet injection of aero-engine bleed air |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211228872.4A CN115573815B (en) | 2022-10-09 | 2022-10-09 | Heat exchange device utilizing jet injection of aero-engine bleed air |
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| CN115573815A CN115573815A (en) | 2023-01-06 |
| CN115573815B true CN115573815B (en) | 2024-10-18 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN106741967A (en) * | 2016-11-30 | 2017-05-31 | 中国直升机设计研究所 | A kind of controllable air circulation system of injection radiating |
| CN216943568U (en) * | 2021-10-20 | 2022-07-12 | 中国航空工业集团公司沈阳飞机设计研究所 | Air inlet injection heat dissipation device |
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| US6250061B1 (en) * | 1999-03-02 | 2001-06-26 | General Electric Company | Compressor system and methods for reducing cooling airflow |
| US7861512B2 (en) * | 2006-08-29 | 2011-01-04 | Pratt & Whitney Canada Corp. | Turbofan bypass duct air cooled fluid cooler installation |
| FR3060057B1 (en) * | 2016-12-14 | 2019-08-30 | Safran Aircraft Engines | FLUIDIC CIRCUIT IN A TURBOMACHINE |
| CN108362025B (en) * | 2018-03-27 | 2023-10-31 | 南京工业大学 | An airborne spray cooling system that uses phase change materials to cool the spray medium and microchannel heat exchangers to prevent failure |
| CN112377325B (en) * | 2020-11-09 | 2022-06-03 | 北京航空航天大学 | Hypersonic strong precooling turbine-based stamping combined engine |
| CN114704382A (en) * | 2022-04-24 | 2022-07-05 | 中国航发沈阳发动机研究所 | Aircraft engine thermal management method and architecture |
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Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106741967A (en) * | 2016-11-30 | 2017-05-31 | 中国直升机设计研究所 | A kind of controllable air circulation system of injection radiating |
| CN216943568U (en) * | 2021-10-20 | 2022-07-12 | 中国航空工业集团公司沈阳飞机设计研究所 | Air inlet injection heat dissipation device |
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