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High performance supersonic bleed inlet

机译:高性能超声波放气入口

摘要

An inlet bleed system for a supersonic aircraft engine having a longitudinally downstream extending inlet bounded by a boundary wall that in part defines a supersonic flowpath through the inlet, a transversely extending boundary layer scoop extends into a boundary layer region of the flowpath and has an upstream facing bleed aperture, and a shock generating means for generating a shockwave in a supersonic flow in the flowpath such that the shockwave passes through the bleed aperture. One embodiment provides a scoop which extends a height above the wall such that it is operable to scoop off no more than a sufficient amount of a boundary layer flow that would exist in the boundary region and be momentum deficient relative to predetermined conditions that would exist downstream of the scoop under supersonic operating conditions. Another embodiment provides for the scoop to be disposed a throat section of the inlet wherein the aperture located is just upstream of the normal shock location.
机译:用于超音速飞机发动机的进气放气系统,其具有由边界壁界定的纵向下游延伸的进气口,该边界壁部分地限定了通过进气口的超音速流路,横向延伸的边界层勺延伸到流路的边界层区域中并且具有上游面对放气孔,以及一个冲击发生装置,用于在流动路径中的超音速流中产生冲击波,从而使冲击波穿过放气孔。一个实施例提供了一种勺子,该勺子在壁上延伸一个高度,使得它可挖出不超过边界区域中存在的足够量的边界层流,并且相对于下游存在的预定条件而言动量不足。在超音速工作条件下的铲斗另一个实施例提供了将勺子布置在入口的喉部,其中所定位的孔正好在正常冲击位置的上游。

著录项

  • 公开/公告号US5397077A

    专利类型

  • 公开/公告日1995-03-14

    原文格式PDF

  • 申请/专利权人 GENERAL ELECTRIC COMPANY;

    申请/专利号US19940205967

  • 发明设计人 PAUL H. KUTSCHENREUTER JR.;

    申请日1994-03-03

  • 分类号B64D33/02;

  • 国家 US

  • 入库时间 2022-08-22 04:05:18

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