CN104760703B - A kind of punching engine cooling body - Google Patents
A kind of punching engine cooling body Download PDFInfo
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- CN104760703B CN104760703B CN201510101473.5A CN201510101473A CN104760703B CN 104760703 B CN104760703 B CN 104760703B CN 201510101473 A CN201510101473 A CN 201510101473A CN 104760703 B CN104760703 B CN 104760703B
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- air inlet
- punching engine
- cooling duct
- cooling
- enging cabin
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Abstract
The present invention discloses a kind of punching engine cooling body, is related to engine cool technical field, can be as the setting of cooling body causes the problem of Stealth Fighter difference in punching engine.The punching engine cooling body of the present invention is included cooling duct and is connected and be arranged on the first air inlet of internal body, the second air inlet and gas outlet with cooling duct；Second air inlet is arranged on landing gear compartment, connect with cooling duct, when hatch door that can be in aircraft in low speed slide and landing gear compartment is not turned off state, extraneous air-flow can flow into cooling duct via landing gear compartment, enging cabin is cooled down, simultaneously, it is not necessary to open up extra air inlet outside airframe, to ensure the Stealth Fighter of aircraft.
Description
Technical field
The present invention relates to engine cool technical field, more particularly to a kind of punching engine cooling body.
Background technology
Enging cabin cooling be in order to cool down enging cabin airframe structure and set annex in the enging cabin, prevent
Accumulation of the flammable gas in enging cabin, therefore, the cooling of enging cabin is extremely important.Enging cabin and engine it
Between be provided with cooling duct, extend at the gas outlet at engine rear portion, by the stream of cooling duct internal gas
The dynamic heat for taking away enging cabin, so as to realize enging cabin cooling.
As shown in fig. 1, be a part of enging cabin 1 structural representation, generally, be in aircraft engine intake 4
Bypass position at open up air inlet 9, connect with cooling duct 3 so that a part of bypass gas flow in air intake duct 4 flows through cooling
Passage 3, realizes cooling.But, when particularly aircraft in slide such low-speed condition when, the bypass in air intake duct 4
Air-flow velocity is low, may cannot be introduced into the cooling that enging cabin realized by enging cabin.Therefore, further again in airframe external-open
If air inlet 9, while also arranging air inlet radome fairing 91 at air inlet, air inlet is connected with the cooling duct 3 in enging cabin,
So that during aircraft low-speed operations, the air-flow of engine body exterior can flow through cooling duct 3, realize cooling.But, extra-organismal air inlet
Radome fairing 91 can destroy the Stealth Fighter of aircraft again.
Content of the invention
The present invention provides a kind of punching engine cooling body, can solve the problem that setting due to cooling body in punching engine
Putting causes the problem of Stealth Fighter difference.
For reaching above-mentioned purpose, the present invention is adopted the following technical scheme that：
A kind of punching engine cooling body, including：
Cooling duct, is made up of the outer wall of enging cabin inwall and the punching engine in the enging cabin；
Gas outlet, is arranged on the enging cabin bulkhead at the tail position of the punching engine, described gives vent to anger
Mouth one end is connected with the cooling duct, and the other end is in communication with the outside；
First air inlet, on the bulkhead of the air intake duct for being arranged on the close described punching engine of the enging cabin, institute
The one end for stating the first air inlet is connected with the air intake duct, and the other end is connected with the cooling duct；
Second air inlet, is arranged on the bulkhead of close described cooling duct of landing gear compartment, second air inlet
One end is connected with the landing gear compartment, and the other end is connected with the cooling duct.
Further, the cooling duct is in the cross section on the punching engine axis direction.
Further, the inner surface of the cooling duct is made as smooth cambered surface.
Further, first air inlet include multiple, in the plane perpendicular to the punching engine axis direction
Inside annularly it is uniformly distributed.
In the punching engine cooling body that the present invention is provided, the second air inlet on landing gear compartment is connected with cooling duct
Logical, can be in aircraft in low speed slide and when the hatch door of landing gear compartment is not turned off state, extraneous air-flow can be via rising and falling
Frame cabin flows into cooling duct, and enging cabin is cooled down, while, it is not necessary to extra air inlet is opened up outside airframe,
To ensure the Stealth Fighter of aircraft.
Description of the drawings
Fig. 1 is the use state schematic diagram of existing punching engine cooling body；
Fig. 2 is the use state schematic diagram of punching engine cooling body according to an embodiment of the invention.
Specific embodiment
Below in conjunction with the accompanying drawings the present invention is described in detail.
As depicted in figs. 1 and 2, the punching engine cooling body of the present invention, including cooling duct 3 and and cooling duct
First air inlet 5 of 3 connections, the second air inlet 8 and gas outlet 6.
Cooling duct 3 is the outer wall structure of the punching engine 2 by 1 inwall of enging cabin and in the enging cabin 1
Become.Cooling duct 3 can be that identical with cooling duct of the prior art 3 in Fig. 1 (in Fig. 1 and Fig. 2, identical label can generation
Table identical part), can be multiple suitable shapes and structure.
In the present embodiment, cooling duct 3 is in the cross section on 2 axis direction of punching engine, Neng Goujin
One step increases the contact area with punching engine 2, improves cooling effect；Also, the inner surface of cooling duct 3 is made as smooth
Cambered surface, can reduce air current flow resistance further, improve cooling effectiveness.
Gas outlet 6 is arranged on 1 bulkhead of enging cabin at the tail position of punching engine 2,6 one end of gas outlet with cold
But passage 3 is connected, and the other end is in communication with the outside.
First air inlet 5 is arranged on the bulkhead of the air intake duct 4 of the close punching engine 2 of enging cabin 1, the first air inlet
One end of mouth 5 is connected with air intake duct 4, and the other end is connected with cooling duct 3.In addition, in the present embodiment, the first air inlet 5 includes
Multiple, annularly it is uniformly distributed in the plane perpendicular to 2 axis direction of punching engine, air flow rate can be increased, and
Reduce gas-flow resistance, by cooling effectiveness.When normal (at a high speed) flight of aircraft, the part entered in air intake duct 4 bypasses gas
Stream can flow through the first air inlet 5 and enter cooling duct 3, finally flow out from the gas outlet 6 of afterbody, realize the cold of enging cabin 1
But.
Second air inlet 8 is arranged on the bulkhead of close cooling duct 3 of landing gear compartment 7, one end of the second air inlet 8 with
Landing gear compartment 7 is connected, and the other end is connected with cooling duct 3.Landing gear compartment 7 is usually located at 1 front portion of enging cabin, when aircraft is in
Low speed slide and (hatch door of similar landing gear compartment 7 is not closed when undercarriage is not packed up, the hatch door of landing gear compartment 7 is not turned off state
The low-speed condition that closes), extraneous air-flow can enter landing gear compartment 7 from hatch door, then flow into cooling via the second air inlet 8
Passage 3, finally flows out from gas outlet 6, enging cabin is cooled down.When further, using such structure, can cancel
Extra air inlet 9 and air inlet radome fairing 91 is opened up outside airframe, so as to strengthen the Stealth Fighter of aircraft.
The above, the only specific embodiment of the present invention, but protection scope of the present invention is not limited thereto, and any
Those familiar with the art the invention discloses technical scope in, change or replacement can be readily occurred in, should all be contained
Cover within protection scope of the present invention.Therefore, protection scope of the present invention described should be defined by scope of the claims.
Claims (4)
1. a kind of punching engine cooling body, it is characterised in that include：
Cooling duct (3), by enging cabin (1) inwall and the outer wall of the punching engine (2) being located in enging cabin (1)
Constitute；
Gas outlet (6), is arranged on the enging cabin (1) bulkhead at the tail position of the punching engine (2), described
Gas outlet (6) one end is connected with the cooling duct (3), and the other end is in communication with the outside；
First air inlet (5), is arranged on the cabin of the air intake duct (4) of the close described punching engine (2) of the enging cabin (1)
On wall, the one end of the first air inlet (5) is connected with the air intake duct (4), and the other end is connected with the cooling duct (3)；
Second air inlet (8), is arranged on the bulkhead of close described cooling duct (3) of landing gear compartment (7), second air inlet
One end of mouth (8) is connected with the landing gear compartment (7), and the other end is connected with the cooling duct (3).
2. punching engine cooling body according to claim 1, it is characterised in that cooling duct (3) are vertical
Cross section on the punching engine (2) axis direction.
3. punching engine cooling body according to claim 1, it is characterised in that the interior table of cooling duct (3)
Face is made as smooth cambered surface.
4. punching engine cooling body according to claim 1, it is characterised in that the first air inlet (5) include
Multiple, annularly it is uniformly distributed in the plane perpendicular to the punching engine (2) axis direction.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510101473.5A CN104760703B (en) | 2015-03-09 | 2015-03-09 | A kind of punching engine cooling body |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510101473.5A CN104760703B (en) | 2015-03-09 | 2015-03-09 | A kind of punching engine cooling body |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104760703A CN104760703A (en) | 2015-07-08 |
| CN104760703B true CN104760703B (en) | 2017-03-08 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510101473.5A Active CN104760703B (en) | 2015-03-09 | 2015-03-09 | A kind of punching engine cooling body |
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| CN (1) | CN104760703B (en) |
Families Citing this family (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104989550B (en) * | 2015-07-22 | 2018-01-30 | 北京航空航天大学 | Scramjet engine liquid nitrogen cooling system |
| CN105730701A (en) * | 2016-02-18 | 2016-07-06 | 江西洪都航空工业集团有限责任公司 | Secondary flow system capable of changing secondary flow inlet area |
| CN106043714B (en) * | 2016-06-07 | 2018-07-17 | 南京航空航天大学 | A kind of cooling air inlet self-regulation helicopter engine core cabin based on unidirectional memorial alloy |
| CN106672248A (en) * | 2016-12-26 | 2017-05-17 | 中国航空工业集团公司西安飞机设计研究所 | Ejection structure |
| CN110901930A (en) * | 2019-12-06 | 2020-03-24 | 西安爱生技术集团公司 | Rear-mounted ventilation cooling device of piston engine |
| CN112455700A (en) * | 2020-11-25 | 2021-03-09 | 中国航空工业集团公司沈阳飞机设计研究所 | Engine compartment cooling device |
| CN112627983B (en) * | 2020-12-25 | 2022-02-22 | 中国人民解放军国防科技大学 | RBCC engine inner flow channel and RBCC engine |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2652509B2 (en) * | 1993-12-28 | 1997-09-10 | 川崎重工業株式会社 | Scramjet engine intake cover device |
| FR2829193B1 (en) * | 2001-08-30 | 2005-04-08 | Snecma Moteurs | AIR COLLECTION SYSTEM OF A COMPRESSOR |
| DE102007061588B4 (en) * | 2007-12-20 | 2011-07-21 | Airbus Operations GmbH, 21129 | Aircraft cooling system |
| CN102155331A (en) * | 2011-05-05 | 2011-08-17 | 西北工业大学 | Turboramjet combined engine based on knocking combustion |
| CN102756807A (en) * | 2012-07-06 | 2012-10-31 | 中国航空工业集团公司西安飞机设计研究所 | Structure and application method of punching air inlet channel shared by liquid cooling system and environmental control system of airplane |
| CN203906118U (en) * | 2014-03-31 | 2014-10-29 | 冯加伟 | Gas cooling system for turbine-based combined-cycle engine |
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| CN104760703A (en) | 2015-07-08 |
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