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    • 8. 发明申请
    • INTEGRATED ENGINE EXHAUST SYSTEMS AND METHODS FOR DRAG AND THERMAL STRESS REDUCTION
    • 集成式发动机排气系统及其应用和减少热应力的方法
    • WO2008054500A2
    • 2008-05-08
    • PCT/US2007008696
    • 2007-04-06
    • BOEING COSHMILOVICH ARVINYADLIN YORAMSMITH DAVID MCLARK ROGER W
    • SHMILOVICH ARVINYADLIN YORAMSMITH DAVID MCLARK ROGER W
    • B64D33/06F02K1/06F02K3/06F05D2250/14Y02T50/671
    • Integrated engine exhaust systems and methods for reducing drag and thermal loads are disclosed. In one embodiment, a propulsion system includes an engine installation configured to be mounted on a wing assembly of an aircraft. The engine installation includes an engine, and an exhaust system operatively coupled to the engine. The exhaust system includes at least one nozzle configured to exhaust an exhaust flow from the engine. The nozzle includes a variable portion configured to vary an exit aperture of the nozzle from a first shape to a second shape to change a flowfield shape of at least a portion of the nozzle flowfield proximate the wing assembly, thereby reducing at least one of drag and thermal loading on the wing assembly. In a further embodiment, the exhaust system includes an inner nozzle that exhausts a core exhaust flow, and an outer nozzle that exhausts a secondary exhaust flow, the outer nozzle having the variable portion configured to vary the exit aperture of the outer nozzle.
    • 公开了用于减少阻力和热负荷的集成发动机排气系统和方法。 在一个实施例中,推进系统包括构造成安装在飞行器的翼组件上的发动机装置。 发动机安装包括发动机和可操作地联接到发动机的排气系统。 排气系统包括至少一个喷嘴,其构造成排出来自发动机的排气流。 喷嘴包括可变部分,其被配置为将喷嘴的出口孔从第一形状改变到第二形状,以改变靠近翼组件的喷嘴流场的至少一部分的流场形状,从而减少阻力和 机翼组件上的热负荷。 在另一个实施例中,排气系统包括排出核心排气流的内部喷嘴和排出二次排气流的外部喷嘴,外部喷嘴具有可变部分,以改变外部喷嘴的出口孔径。