Airframe outer air entraining device based on hypersonic aircraft spray pipe cooling

A technology for nozzle cooling and aircraft body, applied in the direction of jet propulsion devices, machines/engines, etc., can solve problems affecting the performance of other components, difficult to ensure the amount of bleed air, etc., and achieve the effect of increasing the Mach number
CN112648109AActive Publication Date: 2021-04-13SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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Patent Information

Authority / Receiving Office
CN Β· China
Patent Type
Applications(China)
Current Assignee / Owner
SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
Publication Date
2021-04-13

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Abstract

The invention belongs to the technical field of hypersonic aircraft design, and particularly relates to an airframe outer air entraining device based on hypersonic aircraft spray pipe cooling. A lower web plate is arranged on the lower wall surface of an airframe to form a cooling passage with the airframe, an air inlet is formed in the front end of the cooling passage, an exhaust port is formed in the rear end of the cooling passage, an air inlet compression throat is arranged at the air inlet, the lower wall surface of the airframe forms the upper wall surface of the air inlet compression throat, an air entraining device lower wall surface of the air inlet compression throat is formed at the front end of the lower web plate, the upper wall surface of the exhaust port is a spray pipe outer wall surface, and the lower wall surface of the exhaust port is formed by the rear end of the lower web plate. According to the airframe outer air entraining device, high-pressure and low-temperature gas can be provided through the air inlet compression pipeline, the entrained gas passes through the outer wall surface of a high-temperature spraying pipe, on one hand, the spraying pipe is cooled and protected, on the other hand, the gas is heated to generate high-temperature gas to be exhausted, the Mach number of exhaust gas is increased, and then exhaust thrust is generated.
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Description

technical field

[0001] The present application belongs to the technical field of hypersonic aircraft design, and in particular relates to an external bleed air device based on nozzle cooling of a hypersonic aircraft. Background technique

[0002] The nozzle is an exhaust system necessary for the aircraft propulsion device, and it is an essential part of the aircraft to ensure the normal operation of the engine. At the same time, because the nozzle is connected to the rear of the high-temperature and high-pressure combustion chamber, its working environment is quite harsh, and the nozzle can be reused. Tubes generally use superalloys and regenerative cooling methods to cool the nozzles, and disposable nozzles generally use carbon-carbon materials that are ablation materials. Due to the cost requirements and the repeated use requirements of the aircraft, active cooling is generally adopted to reduce the wall temperature of the nozzle and ensure the life of the nozzle. And as ...

Claims

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