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1. 发明授权

US6151883A Aircraft propulsive power unit thrust reverser with separation delay means 失效
标题翻译：具有分离延迟装置的飞机推进动力装置推力反向器
公开(公告)号：US6151883A
公开(公告)日：2000-11-28
申请号：US880949
申请日：1997-06-23
申请人： Michael John Hatrick , Edward Maurice Ashford , Finbarr McEvoy
发明人： Michael John Hatrick , Edward Maurice Ashford , Finbarr McEvoy
IPC分类号： F02K1/72 , F15D1/12 , F02K3/02
CPC分类号： F02K1/72 , F15D1/12 , Y02T50/671
摘要： In an aircraft propulsive power unit a thrust reversing arrangement includes a flow redirecting structure having a flow redirecting downstream wall against which gaseous fluid flow in a first flow direction impinges to turn the flow into a second flow direction to produce reverse thrust and an upstream wall round which the fluid flow turns and which has a boundary surface so formed as to support adherence of a boundary layer of the redirected fluid flow at the boundary surface. The upstream wall is provided with projecting elements to generate vortices which prevent or delay separation of the boundary layer from the boundary surface of the upstream wall. Alternatively, the upstream wall is formed with a plurality of flow apertures which are connected by a duct to a pressure differential region or source to cause gaseous fluid to flow through the boundary surface of the upstream wall to prevent or delay separation of the boundary layer.
摘要翻译：在飞行器推进动力单元中，推力反向装置包括流动重定向结构，其具有流向重定向的下游壁，第一流动方向上的气体流体流动朝着第一流动方向撞击以将流转向第二流动方向以产生反向推力和上游侧壁其流体流动转动并且具有如此形成的边界表面，以支持边界层处的重定向流体流的边界层的粘附。上游壁设置有突出元件以产生防止或延迟边界层与上游壁的边界表面分离的涡流。或者，上游壁形成有多个流动孔，其通过管道连接到压差区域或源，以使气体流体流过上游壁的边界表面以防止或延迟边界层的分离。

2. 发明授权

US06663042B2 Aircraft propulsive power unit 有权
公开(公告)号：US06663042B2
公开(公告)日：2003-12-16
申请号：US09974720
申请日：2001-10-09
申请人： Michael John Hatrick , Joel David Bennett , Finbarr McEvoy , Hugh Keith Campbell , William Edwin Beattie
发明人： Michael John Hatrick , Joel David Bennett , Finbarr McEvoy , Hugh Keith Campbell , William Edwin Beattie
IPC分类号： F02K304
CPC分类号： F02K1/72 , B64D33/04 , F02K1/566 , F02K3/04 , F05D2240/14
摘要： A thrust reversing arrangement for an aircraft turbofan propulsive power unit includes a flow redirecting structure which has reverse flow enhancing sub-structures comprising: (i) a cavity which is so dimensioned as to generate a back pressure which supports redirection of flow; (ii) a cascade assembly which provides a flow control slot so dimensioned as to optimize reverse thrust for predetermined fan duct flow conditions; (iii) an obstructing duct wall portion having a leading edge so positioned as to form a leakage slot providing controlled leakage of forward flow; (iv) a box structure, the dimensions of which are such as to optimize back pressure in the cavity; and (v) provision for gaseous fluid under static pressure from the fan duct to load the redirecting structure to the inoperative position.

3. 发明授权

US06869046B2 Aircraft propulsive power unit 有权
标题翻译：飞机推进动力装置
公开(公告)号：US06869046B2
公开(公告)日：2005-03-22
申请号：US10261832
申请日：2002-09-30
申请人： Finbarr McEvoy
发明人： Finbarr McEvoy
IPC分类号： B64D29/04 , B64D29/08 , B64D27/00
CPC分类号： B64D29/04 , B64D29/08
摘要： An aircraft having a propulsive power unit supported in a fuselage mounted configuration and including an engine and a nacelle structure housing the engine. The nacelle structure is provided with upper and lower displaceable nacelle portions, such as thrust reverser cowls and fan cowl doors which are displaceable between closed dispositions which they occupy during operational conditions of the aircraft and open dispositions which they take up to provide access to engine components. The upper and lower nacelle portions are so mounted as to be displaceable to their open and closed dispositions in movements in which one is assisted by gravitational force and the other is displaced against gravitational force. A force transfer mechanism is provided for transfer during opening and closing movements of the nacelle portions of gravitational force assisting displacement of one of the nacelle portions to assist in displacement of the other nacelle portion being displaced against gravitational force.
摘要翻译：具有支撑在机身安装构造中的推进动力单元的飞机，并且包括容纳发动机的发动机和机舱结构。机舱结构设置有上部和下部可移动机舱部分，例如推力反向器整流罩和风扇整流罩门，其可在位于飞行器的操作条件期间占据的关闭配置之间移动，并且它们占用以提供对发动机部件的接近。上部和下部机舱部分被安装成在其中一个由重力辅助的运动中可移动到它们的打开和关闭的位置，另一个被重力作用移位。提供力传递机构用于在重力的机舱部分的打开和关闭运动期间传递，以帮助机舱中的一个机舱部分的位移，以帮助排除反重力的另一个机舱部分的位移。

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