首页> 外国专利> Apparatus and method for reduction of jet noise from turbofan engines having separate bypass and core flaws

Apparatus and method for reduction of jet noise from turbofan engines having separate bypass and core flaws

机译:减少具有分开的旁路和核心缺陷的涡轮风扇发动机的喷射噪声的装置和方法

摘要

An exhaust flow system for use with a turbofan jet engine that provides separate fan flow and core flow streams that are not mixed. The system includes a fan nozzle and a primary flow nozzle. The primary flow nozzle includes a downstream edge portion that is either beveled with one or more beveled surfaces, or that contains a curving edge surface or a combination of a beveled edge and a curved edge to help direct noise generated by the jet engine upwardly away from a ground surface during take-off and landing procedures. The primary exhaust nozzle can also be orientated with an elongated lip portion thereof formed by the beveled edge surface such that the lip portion is orientated between a top dead center and a bottom dead center position, to thus help direct noise away from a cabin area of a fuselage of a mobile platform during cruise conditions.
机译:与涡扇喷气发动机一起使用的排气系统,其提供分开的风扇流和没有混合的核心流。该系统包括风扇喷嘴和主流喷嘴。主流喷嘴包括下游边缘部分,该下游边缘部分被一个或多个倾斜表面斜切,或者包含弯曲边缘表面或斜切边缘和弯曲边缘的组合,以帮助将喷气发动机产生的噪声向上引导远离起飞和着陆过程中的地面。主排气喷嘴还可以通过由倾斜的边缘表面形成的细长唇部定向,以使唇部在上止点和下止点位置之间定向,从而帮助将噪音引导至车外区域。巡航条件下移动平台的机身。

著录项

  • 公开/公告号US7836700B2

    专利类型

  • 公开/公告日2010-11-23

    原文格式PDF

  • 申请/专利权人 KRISHNAMURTHY VISWANATHAN;

    申请/专利号US20080013060

  • 发明设计人 KRISHNAMURTHY VISWANATHAN;

    申请日2008-01-11

  • 分类号F02K1/00;

  • 国家 US

  • 入库时间 2022-08-21 18:08:48

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