CN104760703A - Cooling mechanism for ramjet engine - Google Patents
Cooling mechanism for ramjet engine Download PDFInfo
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- CN104760703A CN104760703A CN201510101473.5A CN201510101473A CN104760703A CN 104760703 A CN104760703 A CN 104760703A CN 201510101473 A CN201510101473 A CN 201510101473A CN 104760703 A CN104760703 A CN 104760703A
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Abstract
The invention discloses a cooling mechanism for a ramjet engine, and relates to the technical field of engine cooling. The problem that the stealth performance is poor due to the arrangement of the cooling mechanism in the ramjet engine can be solved. The cooling mechanism for the ramjet engine comprises a cooling channel, a first air inlet, a second air inlet and an air outlet, wherein the first air inlet, the second air inlet and the air outlet are communicated with the cooling channel and are formed in an engine body. The second air inlet is formed in an ear compartment and is communicated with the cooling channel. When an aircraft slides at a low speed and when a compartment door of the ear compartment is not in a closed state, outside air flow can flow into the cooling channel through the ear compartment to cool an engine compartment. Meanwhile, no extra air inlet needs to be formed in the outside of an aircraft body, so that the stealth performance of the aircraft is guaranteed.
Description
Technical field
The present invention relates to engine cooling technical field, particularly relate to a kind of punching engine cooling body.
Background technology
Machinery space cooling is that prevent flammable gas gathering in machinery space, therefore, the cooling of machinery space is extremely important in order to cooled engine cabin airframe structure and annex set in machinery space.Between machinery space and driving engine, be provided with cooling-gallery, extend to the air extractor duct place being positioned at driving engine rear portion always, taken away the heat of machinery space by the flowing of cooling-gallery internal gas, thus realize machinery space cooling.
As shown in fig. 1, be the structural representation of a part of machinery space 1, usually, offer admission port 9 at the bypass position place of aircraft engine intake 4, be communicated with cooling-gallery 3, make a part of bypass gas flow in inlet channel 4 flow through cooling-gallery 3, realize cooling.But, when particularly aircraft be in slide such low-speed condition time, the bypass gas flow flow velocity in inlet channel 4 is low, possibly cannot enter the cooling that machinery space realizes machinery space.Therefore, outside airframe, offer admission port 9 again further, also air inlet fairing 91 is set at admission port place simultaneously, admission port is communicated with the cooling-gallery 3 in machinery space, when making aircraft low-speed operations, the air-flow of engine body exterior can flow through cooling-gallery 3, realizes cooling.But extra-organismal air inlet fairing 91 can destroy again the Stealth Fighter of aircraft.
Summary of the invention
The invention provides a kind of punching engine cooling body, can solve in punching engine because the setting of cooling body causes the problem of Stealth Fighter difference.
For achieving the above object, the present invention adopts following technical scheme:
A kind of punching engine cooling body, comprising:
Cooling-gallery, is made up of the outer wall of machinery space inwall with the punching engine being positioned at described machinery space;
Air extractor duct, be arranged on the described machinery space bulkhead at the tail position place of described punching engine, described air extractor duct one end is communicated with described cooling-gallery, and the other end is in communication with the outside;
First admission port, be arranged on the bulkhead of the inlet channel of the close described punching engine of described machinery space, one end of described first admission port is communicated with described inlet channel, and the other end is communicated with described cooling-gallery;
Second admission port, is arranged on the bulkhead of close described cooling-gallery of landing gear compartment, and one end of described second admission port is communicated with described landing gear compartment, and the other end is communicated with described cooling-gallery.
Further, described cooling-gallery is perpendicular to the cross section on described punching engine axis direction.
Further, the inside face of described cooling-gallery is made as smooth cambered surface.
Further, described first admission port comprises multiple, is uniformly distributed in the form of a ring in the plane perpendicular to described punching engine axis direction.
In punching engine cooling body provided by the invention, the second admission port on landing gear compartment is communicated with cooling-gallery, low speed slide can be at aircraft and the hatch door of landing gear compartment non-closed condition time, extraneous air-flow can flow into cooling-gallery via landing gear compartment, machinery space is cooled, meanwhile, do not need to offer extra admission port outside airframe, to ensure the Stealth Fighter of aircraft.
Accompanying drawing explanation
Fig. 1 is the using state schematic diagram of existing punching engine cooling body;
Fig. 2 is the using state schematic diagram of punching engine cooling body according to an embodiment of the invention.
Detailed description of the invention
Be described in detail of the present invention below in conjunction with accompanying drawing.
As depicted in figs. 1 and 2, punching engine cooling body of the present invention, the first admission port 5, second admission port 8 and the air extractor duct 6 comprising cooling-gallery 3 and be communicated with cooling-gallery 3.
Cooling-gallery 3 is made up of the outer wall of machinery space 1 inwall with the punching engine 2 being positioned at described machinery space 1.Cooling-gallery 3 can be identical with cooling-gallery 3 of the prior art in Fig. 1 (label identical in Fig. 1 with Fig. 2 can represent identical parts), can be multiple applicable shape and structure.
In the present embodiment, cooling-gallery 3, perpendicular to the cross section on punching engine 2 axis direction, can increase the area of contact with punching engine 2 further, improves cooling performance; Further, the inside face of cooling-gallery 3 is made as smooth cambered surface, can reduce air current flow resistance further, improves cooling effectiveness.
Air extractor duct 6 is arranged on machinery space 1 bulkhead at the tail position place of punching engine 2, and air extractor duct 6 one end is communicated with cooling-gallery 3, and the other end is in communication with the outside.
First admission port 5 is arranged on the bulkhead of the inlet channel 4 of the close punching engine 2 of machinery space 1, and one end of the first admission port 5 is communicated with inlet channel 4, and the other end is communicated with cooling-gallery 3.In addition, in the present embodiment, the first admission port 5 comprises multiple, is uniformly distributed in the form of a ring in the plane perpendicular to punching engine 2 axis direction, can strengthen air flow rate, and reduces air-flow resistance, passes through cooling effectiveness.When aircraft normal (at a high speed) flight, a part of bypass gas flow entered in inlet channel 4 can flow through the first admission port 5 and enter cooling-gallery 3, finally flows out from the air extractor duct 6 of afterbody, realizes the cooling of machinery space 1.
Second admission port 8 is arranged on the bulkhead of close cooling-gallery 3 of landing gear compartment 7, and one end of the second admission port 8 is communicated with landing gear compartment 7, and the other end is communicated with cooling-gallery 3.It is anterior that landing gear compartment 7 is usually located at machinery space 1, when aircraft be in low speed slide and alighting gear is not packed up, the hatch door of landing gear compartment 7 non-closed condition time (low-speed condition that the hatch door of similar landing gear compartment 7 is not closed), extraneous air-flow can enter landing gear compartment 7 from hatch door, cooling-gallery 3 is flowed into again via the second admission port 8, finally flow out from air extractor duct 6, machinery space is cooled.Further, when adopting such structure, can cancel and offer extra admission port 9 and air inlet fairing 91 outside airframe, thus strengthen the Stealth Fighter of aircraft.
The above; be only the specific embodiment of the present invention, but protection scope of the present invention is not limited thereto, is anyly familiar with those skilled in the art in the technical scope that the present invention discloses; change can be expected easily or replace, all should be encompassed within protection scope of the present invention.Therefore, protection scope of the present invention should described be as the criterion with the protection domain of claim.
Claims (4)
1. a punching engine cooling body, is characterized in that, comprising:
Cooling-gallery (3), is made up of the outer wall of machinery space (1) inwall with the punching engine (2) being positioned at described machinery space (1);
Air extractor duct (6), be arranged on described machinery space (1) bulkhead at the tail position place of described punching engine (2), described air extractor duct (6) one end is communicated with described cooling-gallery (3), and the other end is in communication with the outside;
First admission port (5), be arranged on the bulkhead of the inlet channel (4) of the close described punching engine (2) of described machinery space (1), one end of described first admission port (5) is communicated with described inlet channel (4), and the other end is communicated with described cooling-gallery (3);
Second admission port (8), be arranged on the bulkhead of close described cooling-gallery (3) of landing gear compartment (7), one end of described second admission port (8) is communicated with described landing gear compartment (7), and the other end is communicated with described cooling-gallery (3).
2. punching engine cooling-gallery according to claim 1, is characterized in that, described cooling-gallery (3) is perpendicular to the cross section on described punching engine (2) axis direction.
3. punching engine cooling-gallery according to claim 1, is characterized in that, the inside face of described cooling-gallery (3) is made as smooth cambered surface.
4. punching engine cooling-gallery according to claim 1, is characterized in that, described first admission port (5) comprises multiple, is uniformly distributed in the form of a ring in the plane perpendicular to described 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 |
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| CN104760703A true CN104760703A (en) | 2015-07-08 |
| CN104760703B CN104760703B (en) | 2017-03-08 |
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| CN201510101473.5A Active CN104760703B (en) | 2015-03-09 | 2015-03-09 | A kind of punching engine cooling body |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104989550A (en) * | 2015-07-22 | 2015-10-21 | 北京航空航天大学 | Liquid-nitrogen cooling system of scramjet engine |
| 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 |
| CN106043714A (en) * | 2016-06-07 | 2016-10-26 | 南京航空航天大学 | Cooling gas inflow self-adjusting engine core engine room based on one-way memory 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 |
| CN112627983A (en) * | 2020-12-25 | 2021-04-09 | 中国人民解放军国防科技大学 | RBCC engine inner flow channel and RBCC engine |
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| JPH07197855A (en) * | 1993-12-28 | 1995-08-01 | Kawasaki Heavy Ind Ltd | Intake cover device for scram jet engine |
| CA2398422A1 (en) * | 2001-08-30 | 2003-02-28 | Snecma Moteurs | Compressor air drawing off system |
| WO2009080168A1 (en) * | 2007-12-20 | 2009-07-02 | Airbus Operations Gmbh | 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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2015
- 2015-03-09 CN CN201510101473.5A patent/CN104760703B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
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| JPH07197855A (en) * | 1993-12-28 | 1995-08-01 | Kawasaki Heavy Ind Ltd | Intake cover device for scram jet engine |
| CA2398422A1 (en) * | 2001-08-30 | 2003-02-28 | Snecma Moteurs | Compressor air drawing off system |
| WO2009080168A1 (en) * | 2007-12-20 | 2009-07-02 | Airbus Operations Gmbh | 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 |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104989550A (en) * | 2015-07-22 | 2015-10-21 | 北京航空航天大学 | Liquid-nitrogen cooling system of scramjet engine |
| 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 |
| CN106043714A (en) * | 2016-06-07 | 2016-10-26 | 南京航空航天大学 | Cooling gas inflow self-adjusting engine core engine room based on one-way memory alloy |
| 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 |
| CN112627983A (en) * | 2020-12-25 | 2021-04-09 | 中国人民解放军国防科技大学 | RBCC engine inner flow channel and RBCC engine |
| 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 |
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| Publication number | Publication date |
|---|---|
| CN104760703B (en) | 2017-03-08 |
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