A hypersonic aircraft includes one or more leading edge assemblies that are designed to cool the leading edge of certain portions of the hypersonic aircraft that are exposed to high thermal loads, such as extremely high temperatures and/or thermal gradients. Specifically, the leading edge assemblies may include an outer wall tapered to a leading edge or stagnation point. A coolant supply may be in fluid communication with at least one fluid passageway that passes through the outer wall to deliver a flow of cooling fluid to the stagnation point. In addition, a nose cover is positioned at least partially over or within the at least one fluid passageway and is formed from a material that ablates or melts when the leading edge is exposed to a predetermined critical temperature, and the nose cover is configured for restricting the flow of coolant until the nose cover is ablated or melted away.

    高超音速飞行器包括一个或多个前缘组件,一个或多个前缘组件被设计成冷却高超音速飞行器的暴露于例如极高温度和/或热梯度的高热负荷的某些部分的前缘。具体地,前缘组件可以包括渐缩至前缘或停滞点的外壁。冷却剂供应源可以与至少一个流体通道流体连通,至少一个流体通道穿过外壁,以将冷却流体流输送到停滞点。另外,机头罩至少部分地被定位在至少一个流体通道之上或之内,并且由前缘暴露于预定临界温度时会烧蚀或熔化的材料形成,机头罩被构造用于限制冷却剂流,直到机头罩被烧蚀或熔化掉。


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    Titel :

    System and method for cooling leading edge of high speed vehicle


    Weitere Titelangaben:

    用于冷却高速交通工具的前缘的系统和方法


    Beteiligte:

    Erscheinungsdatum :

    2021-05-18


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS



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