CN103538720A - Heat preventing and insulating device of gas inlet path - Google Patents
Heat preventing and insulating device of gas inlet path Download PDFInfo
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- CN103538720A CN103538720A CN201310460888.2A CN201310460888A CN103538720A CN 103538720 A CN103538720 A CN 103538720A CN 201310460888 A CN201310460888 A CN 201310460888A CN 103538720 A CN103538720 A CN 103538720A
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- heat
- insulating device
- proof device
- gas inlet
- heat preventing
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Abstract
The invention discloses a heat preventing and insulating device of a gas inlet path. The heat preventing and insulating device is composed of a soft part (4) and a hard part (5), wherein the soft part is made of aerogel, and the hard part is made of a ceramic material; after respectively processing and forming the soft part (4) of the heat preventing and insulating device and the hard part (5) of the heat preventing and insulating device according to shape and dimension of the gas inlet path independently, connecting glue is coated, and the soft part (4) and the hard part (5) are placed in a high-temperature furnace for burning. The heat preventing and insulating device disclosed by the invention can be used for ensuring that hot gas in a runner is not transferred to a gas inlet equipment bin under the condition that an aircraft flies under higher dynamic pressure and higher mach number.
Description
Technical field
The present invention relates to anti-heat insulation structural in hypersonic aircraft equipment compartment.Can prevent that the high-temperature gas in aircraft inlet channel runner from reaching in aircraft devices cabin by inlet channel runner, guarantee that equipment compartment temperature meets equipment requirement.
Background technology
The hypersonic aircraft that the scramjet engine of take is power has the feature of body/engine integration, under hypersonic flight condition, air-flow is after the compression of inlet channel, the inlet channel runner of flowing through, inlet channel runner is outer to be prevented by solar heat protection covering that external heat from spreading and is handed in equipment compartment, but the high temperature gas flow in inlet channel runner can reach in equipment compartment by the bottom of runner, and below deck equipment is exerted an influence.
In this case, prevent that the high temperature and high pressure gas in inlet channel runner from importing in aircraft devices cabin just particularly crucial.But because inlet duct flow road shape is special-shaped, and general special-shaped anti-thermal insulation material is softer, cannot be fixed on metal covering.
Summary of the invention
The problem that the present invention is directed to prior art existence proposes the anti-heat-proof device of a kind of hypersonic aircraft metal inlet.Can guarantee that aircraft is at high dynamic pressure more, more under High Mach number condition in flight situation, the hot gas in runner can not reach in inlet channel equipment compartment.
The anti-heat-proof device of a kind of metal inlet of the present invention, is partly comprised of soft section, hard; Soft section is that aerogel, hard are partly stupalith; Respectively by anti-heat-proof device soft section and anti-heat-proof device hard part separately according to after the machine-shaping of inlet channel shape and size, be coated with and spread connection glue, put into high temperature furnace and fire.
Further, described connection glue is the red glue of high temperature.Further, described firing temperature is 1000～2000 ℃.
The anti-heat-proof device of a kind of metal inlet of the present invention, its inside face is soft compound type thermal insulation material, available in case heat insulation, and outside is hard ceramic material, can be used for being connected with metal inlet, guarantees the reliable connection of anti-thermal insulation material.Efficiently solve in hypersonic aircraft process of the test, the high-temperature gas of aircraft inlet channel runner is intercepted.
Accompanying drawing explanation
Fig. 1: the present invention is installed on schematic diagram on inlet channel;
Fig. 2: the anti-heat-proof device schematic diagram of the present invention.
The specific embodiment
Below in conjunction with accompanying drawing, the present invention will be further described.
As shown in Figure 1, when high-temperature high-pressure air flow passes through inlet channel runner 1, high-temperature gas is passed to equipment compartment 3 by metal flow passage, so that equipment compartment 3 cabin temperature rises affect the normal operation of equipment.The effect of anti-heat-proof device 2 is exactly to prevent that high temperature is passed in equipment compartment.
As shown in Figure 2, anti-heat-proof device 2 is by anti-heat-proof device soft section 4, and anti-heat-proof device hard part 5 forms.Anti-heat-proof device soft section 4 can intercept scurrying into of high-temperature gas, and its main material is aerogel, and the thick soft section 2 of 10mm can be every the temperature of living 1000 ℃, can need be with different thickness according to required heat insulation temperature; But because matter is soft, cannot realize and being fastenedly connected of metal wall.Anti-heat-proof device hard part 5 has made up this defect, and it has certain strong rigidity, and main material is stupalith, the compressive strength of self
, and may be molded to simple other shaped.Respectively by anti-heat-proof device soft section 4 with anti-heat-proof device hard part 5 separately according to after the machine-shaping of inlet channel shape and size, be coated with and spread connection glue, glue as red in high temperature.Putting into high temperature furnace heats to 1000-2000 ℃ and fires.Fire after end, by the through hole in anti-heat-proof device hard part 5, can realize reliable connection the between anti-heat-proof device 2 and inlet channel runner 1.
This anti-heat-insulating method, can prevent special-shaped air inlet passage runner heat insulation.The soft section 4 of anti-heat-proof device 2 can random molding, and hard part 5 can be carried out according to demand abnormal shape and fired, and can realize reliably bonding with soft section simultaneously.
This heat-proof device can be realized simultaneously and prevent heat insulation to a plurality of runners of same aircraft simultaneously.
The just specific embodiment of this invention that specification sheets is described, various casehistorys do not limit essence of an invention Composition of contents, under technical field reading after specification sheets and can the specific embodiment described in the past made an amendment or is out of shape, and do not deviate from essence of an invention and scope.
Claims (3)
1. the anti-heat-proof device of metal inlet, is comprised of soft section (4), hard part (5); Soft section is that aerogel, hard are partly stupalith; Respectively by anti-heat-proof device soft section (4) with anti-heat-proof device hard part (5) separately according to after the machine-shaping of inlet channel shape and size, be coated with and spread connection glue, put into high temperature furnace and fire.
2. the anti-heat-proof device of a kind of metal inlet as claimed in claim 1, is characterized in that described connection glue is the red glue of high temperature.
3. the anti-heat-proof device of a kind of metal inlet as claimed in claim 1, is characterized in that described firing temperature is 1000～2000 ℃.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310460888.2A CN103538720A (en) | 2013-09-30 | 2013-09-30 | Heat preventing and insulating device of gas inlet path |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310460888.2A CN103538720A (en) | 2013-09-30 | 2013-09-30 | Heat preventing and insulating device of gas inlet path |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103538720A true CN103538720A (en) | 2014-01-29 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310460888.2A Pending CN103538720A (en) | 2013-09-30 | 2013-09-30 | Heat preventing and insulating device of gas inlet path |
Country Status (1)
| Country | Link |
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| CN (1) | CN103538720A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106005445A (en) * | 2016-07-27 | 2016-10-12 | 中国航空工业集团公司西安飞机设计研究所 | Engine structure and airplane with same |
| CN109484656A (en) * | 2018-12-24 | 2019-03-19 | 沈阳旋飞航空技术有限公司 | A kind of engine heat insulation structural for the dynamic unmanned plane of oil |
| CN112829955A (en) * | 2021-03-03 | 2021-05-25 | 上海机电工程研究所 | Aircraft air inlet duct and cabin axial installation area heat seal structure |
| CN113443150A (en) * | 2021-08-30 | 2021-09-28 | 西安航天动力研究所 | Compact unmanned aerial vehicle turbojet engine |
Citations (4)
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| US6488900B1 (en) * | 1998-10-20 | 2002-12-03 | Mesosystems Technology, Inc. | Method and apparatus for air purification |
| US20030141043A1 (en) * | 2002-01-29 | 2003-07-31 | Warburton Robert E. | Heat exchanger panel |
| US6627019B2 (en) * | 2000-12-18 | 2003-09-30 | David C. Jarmon | Process for making ceramic matrix composite parts with cooling channels |
| EP1746257A2 (en) * | 2005-07-19 | 2007-01-24 | United Technologies Corporation | Vehicle and corresponding operating method |
-
2013
- 2013-09-30 CN CN201310460888.2A patent/CN103538720A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6488900B1 (en) * | 1998-10-20 | 2002-12-03 | Mesosystems Technology, Inc. | Method and apparatus for air purification |
| US6627019B2 (en) * | 2000-12-18 | 2003-09-30 | David C. Jarmon | Process for making ceramic matrix composite parts with cooling channels |
| US20030141043A1 (en) * | 2002-01-29 | 2003-07-31 | Warburton Robert E. | Heat exchanger panel |
| EP1746257A2 (en) * | 2005-07-19 | 2007-01-24 | United Technologies Corporation | Vehicle and corresponding operating method |
Non-Patent Citations (1)
| Title |
|---|
| 赵南等: "耐高温气凝胶隔热材料", 《宇航材料工艺》 * |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106005445A (en) * | 2016-07-27 | 2016-10-12 | 中国航空工业集团公司西安飞机设计研究所 | Engine structure and airplane with same |
| CN109484656A (en) * | 2018-12-24 | 2019-03-19 | 沈阳旋飞航空技术有限公司 | A kind of engine heat insulation structural for the dynamic unmanned plane of oil |
| CN109484656B (en) * | 2018-12-24 | 2020-10-27 | 沈阳旋飞航空技术有限公司 | A engine heat insulation structure for oil move unmanned aerial vehicle |
| CN112829955A (en) * | 2021-03-03 | 2021-05-25 | 上海机电工程研究所 | Aircraft air inlet duct and cabin axial installation area heat seal structure |
| CN112829955B (en) * | 2021-03-03 | 2022-07-26 | 上海机电工程研究所 | Aircraft air inlet duct and cabin axial installation area heat seal structure |
| CN113443150A (en) * | 2021-08-30 | 2021-09-28 | 西安航天动力研究所 | Compact unmanned aerial vehicle turbojet engine |
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Application publication date: 20140129 |