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Film cooling system with ejector and method

A technology of film cooling and ejector, which is applied in space vehicle heat protection devices, aerospace safety/emergency devices, aircraft parts, etc. It can solve the problems of simple structure and achieve the effect of increasing quality

Active Publication Date: 2017-06-23
TSINGHUA UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Film cooling and heat protection has all the advantages of sweat cooling and heat protection above, but it is much simpler in structure

Method used

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  • Film cooling system with ejector and method
  • Film cooling system with ejector and method

Examples

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Effect test

Embodiment 1

[0022] Such as figure 1 As shown, this embodiment provides an ejector-containing film cooling system carrying a gaseous coolant, which includes a coolant storage container 1 and an ejector 2 . Wherein, the coolant storage container 1 stores gaseous coolant, and the coolant storage container 1 is arranged inside the hypersonic aircraft. The coolant storage container 1 is connected to the high-pressure inlet of the ejector 2 through the pipeline and the regulating valve 3, and the low-pressure inlet of the ejector 2 is connected to the suction hole 4 on the surface of the aircraft through the pipeline. The outlet of the ejector 2 is connected with several film cooling microholes 5 on the surface of the aircraft through pipelines.

[0023] In a preferred embodiment, the position of the suction hole 4 is not limited, and the position on the surface of the aircraft with a lower atmospheric temperature is preferred.

[0024] In a preferred embodiment, the position of the film cool...

Embodiment 2

[0031] Such as figure 2 As shown, this embodiment provides an ejector-containing film cooling system carrying a liquid coolant, which includes a coolant storage container 1 and an ejector 2 . Wherein, liquid coolant is stored in the coolant storage container 1, and the coolant storage container 1 is arranged inside the hypersonic aircraft. The coolant storage container 1 is connected to the high-pressure inlet of the ejector 2 through a pipeline and a booster pump 6, and the low-pressure inlet of the ejector 2 is connected to the suction hole 4 on the surface of the aircraft through a pipeline. The outlet of the ejector 2 is connected with several film cooling microholes 5 on the surface of the aircraft through pipelines.

[0032] In a preferred embodiment, the position of the suction hole 4 is not limited, and the position on the surface of the aircraft with a lower atmospheric temperature is preferred.

[0033] In a preferred embodiment, the position of the film cooling m...

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PUM

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Abstract

The invention relates to a film cooling system with an ejector and a method. The film cooling system comprises a coolant storage container arranged inside an aircraft, a suction hole and a plurality of film cooling micropores which are formed in the surface of the aircraft and the ejector connected with the coolant storage container, the suction hole and the film cooling micropores. According to the method, a high-pressure coolant is adopted as working fluid of the ejector, low-pressure fluid outside the aircraft is sucked, fluid after being mixed is used as cooling fluid of film cooling, after the mixed fluid flows out of the outlet of the ejector and arrives at the plurality of film cooling micropores on the surface of the aircraft, a cooling film is formed in the surface of the aircraft, and thermal protection of the high-temperature surface of a hypersonic aircraft is achieved.

Description

technical field [0001] The invention relates to a thermal protection system and method for an aircraft surface, in particular to a film cooling system and method with an ejector suitable for the high-temperature surface of a hypersonic aircraft. Background technique [0002] With the development of aerospace technology, the speed of aircraft continues to increase. With the increase of flight speed, severe aerodynamic heating makes the outer surface of the aircraft bear extremely high heat flux density, the temperature rises sharply, and a thermal barrier appears, which threatens the safety of the aircraft in severe cases. Therefore, developing an efficient thermal protection system is an urgent problem to be solved in the development of hypersonic vehicles. [0003] Regarding the thermal protection of hypersonic vehicles, there are currently many research methods: passive thermal protection (ablation cooling, heat insulation and heat protection, heat sink heat protection; r...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/58B64D45/00
CPCB64D45/00B64G1/58
Inventor 祝银海姜培学
Owner TSINGHUA UNIV
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