The invention discloses a rotary detonation combustion chamber, an aircraft attitude control engine and application of the rotary detonation combustion chamber and the aircraft attitude control engine. The rotary detonation combustion chamber with the thermal protection structure comprises a housing and a combustion chamber body defined by the housing, the combustion chamber body is provided with a combustion section and a spray pipe section, the housing is provided with an oxidant injection structure and a fuel injection structure which are communicated with the combustion section, and a regeneration cooling channel is formed in the housing. The regenerative cooling channel communicates with the fuel injection structure, fuel is injected into the combustion chamber through the regenerative cooling channel and the fuel injection structure, and the regenerative cooling channel is arranged on the outer side of the combustion chamber and is in heat conduction fit with the housing. Fuel flowing through the regenerative cooling channel can exchange heat with the internal environment of the combustion chamber to be preheated, and the fuel entering the combustion chamber from the fuel injection structure forms a cooling film for isolating high-temperature fuel gas on the inner wall face of the combustion chamber while participating in combustion.
本发明公开了一种旋转爆轰燃烧室、飞行器姿控发动机及其应用。带热防护结构的旋转爆轰燃烧室包括:罩壳以及由所述罩壳围合形成的燃烧室,所述燃烧室具有燃烧段和喷管段,所述罩壳上设置有与所述燃烧段连通的氧化剂注入结构和燃料注入结构,以及,再生冷却通道,所述再生冷却通道与所述燃料注入结构相连通,燃料经所述再生冷却通道以及所述燃料注入结构被注入至所述燃烧室,所述再生冷却通道设置在所述燃烧室的外侧且与所述罩壳导热配合,流经所述再生冷却通道的燃料能够与所述燃烧室的内部环境发生热量交换而被预加热,并且,自所述燃料注入结构进入所述燃烧室的燃料在参与燃烧的同时,还在所述燃烧室的内壁面形成隔绝高温燃气的冷却薄膜。
Rotary detonation combustion chamber, aircraft attitude control engine and application thereof
旋转爆轰燃烧室、飞行器姿控发动机及其应用
2025-02-14
Patent
Electronic Resource
Chinese
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