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1. 发明授权

US5101621A Integrated corner for ducted fan engine shrouds 失效
标题翻译：风扇发动机罩的集成角
公开(公告)号：US5101621A
公开(公告)日：1992-04-07
申请号：US411991
申请日：1989-09-25
申请人： Henry Mutch
发明人： Henry Mutch
IPC分类号： B29D24/00 , B64D29/00
CPC分类号： B29D24/005 , B64D29/00 , Y10T428/24149
摘要： An engine shroud with integral honeycomb panel corners for use in the thrust reverser region of ducted fan gas turbine engines. The integral shroud is useful in a turbine engine having a core engine surrounded by an engine casing and nacelle, with a fan at the inlet directing air flow into the bypass duct between core engine and engine nacelle. The shroud basically consists of right and left ducts each having an approximately semicircular cross-section with radial flanges extending from the duct edges. The flanges permit the halves to be fastened together to produce a tubular shroud adapted to surround a gas turbine engine and form the inner wall of a bypass duct. The disclosed shroud eliminates the prior complex corner fittings connecting the semicircular center portion of the shroud to the extending flanges and provides simple, integral corners.
摘要翻译：具有整体蜂窝板角的发动机罩，用于管道式风机燃气轮机的推力反向器区域。整体护罩可用于具有由发动机壳体和机舱包围的核心发动机的涡轮发动机，入口处的风扇将空气流引导到核心发动机和发动机机舱之间的旁路管道。护罩基本上由右和左管道组成，每个管道具有大致半圆形的横截面，其中径向凸缘从管道边缘延伸。凸缘允许半部紧固在一起以产生适于围绕燃气涡轮发动机并形成旁通管道的内壁的管状护罩。所公开的护罩消除了将罩的半圆形中心部分与延伸法兰连接的现有复杂的角配件，并且提供了简单的整体角。

2. 发明授权

US4998409A Thrust reverser torque ring 失效
标题翻译：推力反向转矩环
公开(公告)号：US4998409A
公开(公告)日：1991-03-12
申请号：US411992
申请日：1989-09-25
申请人： Henry Mutch
发明人： Henry Mutch
IPC分类号： F02K1/72
CPC分类号： F02K1/72 , Y02T50/672
摘要： A thrust ring assembly for use in a thrust reverser system for a gas turbine engine. The ring assembly is useful in a turbine engine having a core engine surrounded by an engine casing and nacelle, with a fan at the inlet directing air flow into the bypass duct between core engine and nacelle. The thrust reverser basically comprises at least one opening through the engine casing and nacelle, a turning vane cascade in the opening, a cover movable by an actuator between positions covering and uncovering the opening and at least one blocker door movable between a position allowing flow through the bypass duct and a position diverting flow to the turning vane cascade. The actuator and cascade are severely aerodynamically loaded during thrust reversal. The improved thrust ring assembly carriers those loads and transfers them to the engine casing. The forward ends of the cascade and actuator are secured to a bulkhead ring which is secured to the base of a frustoconical ring. An inwardly directed torque ring V-blade at the apex of the frustoconical ring is received in a groove in an engine ring secured to the engine casing to transfer the loads. A curved ramp ring secured to the inner edges of said bulkhead ring and torque ring smoothes air flow from the bypass duct to the cascade.
摘要翻译：用于燃气涡轮发动机的推力反向器系统中的推力环组件。环组件可用于具有由发动机壳体和机舱围绕的核心发动机的涡轮发动机，入口处的风扇将空气流引导到核心发动机和机舱之间的旁路管道。推力反向器基本上包括通过发动机壳体和机舱的至少一个开口，开口中的转动叶片级联，通过致动器可以在覆盖和露出开口的位置之间移动的盖子，以及至少一个阻挡门，其可在允许流过旁路管道和转向叶片级联的位置转向。在推力反转过程中，执行器和级联严重受空气动力学负载。改进的推力环组件承载那些负载并将它们传递到发动机壳体。级联和致动器的前端固定到固定到截头圆锥形环的基部的隔板环上。在截头圆锥形环的顶点处的向内定向的扭矩环V形叶片被容纳在固定到发动机壳体上的发动机环的凹槽中以传递负载。固定在所述隔板环和扭矩环的内边缘上的弯曲斜坡环平滑了从旁路管道到级联的空气流。

3. 发明授权

US5054281A Gas turbine engine compartment vent system 失效
标题翻译：燃气轮机发动机舱通风系统
公开(公告)号：US5054281A
公开(公告)日：1991-10-08
申请号：US411643
申请日：1989-09-25
申请人： Henry Mutch
发明人： Henry Mutch
IPC分类号： B64D33/08 , F02C7/12
CPC分类号： F02C7/12 , B64D33/08 , Y02T50/671 , Y02T50/675
摘要： A system for selectively venting cool bypass duct air into selected locations between a gas turbine engine and the engine shroud. The venting system is useful in a turbine engine having a core engine surrounded by an engine casing and nacelle, with a fan at the inlet directing air flow into the bypass duct between core engine and engine casing. The venting system basically comprises tubes inserted in holes in the engine shroud which separates the bypass duct from the engine compartment. Often sensors, electronic components or the like are advantageously located in the engine compartment. However, elevated temperatures in the engine compartment often damages or degrades those components. The vent tubes are positioned so as to direct cool air onto those components. A large number of vents may be provided in the shroud as manufactured, each plugged at manufacture, with only those opened which are needed for a specific engine with specifically located heat sensitive components.
摘要翻译：用于选择性地将燃气涡轮发动机和发动机罩之间的旁路管道空气排放到选定位置的系统。排气系统在具有由发动机壳体和机舱包围的核心发动机的涡轮发动机中是有用的，在入口处的风扇将空气流引入到核心发动机和发动机壳体之间的旁路管道中。排气系统基本上包括插入发动机罩中的孔中的管，其将旁通管与发动机舱分离。通常，传感器，电子部件等有利地位于发动机室中。然而，发动机室中的高温通常会损坏或降解这些部件。通风管被定位成将冷空气引导到这些部件上。可以在制造的护罩中提供大量通风孔，每个通风口都在制造时插入，只有那些打开的特定发动机需要具有特定位置的热敏组件。

4. 发明授权

US4005836A Target thrust reverser 失效
标题翻译：目标推力反向器
公开(公告)号：US4005836A
公开(公告)日：1977-02-01
申请号：US643493
申请日：1975-12-22
申请人： Henry Mutch
发明人： Henry Mutch
IPC分类号： B64C25/42 , B64D33/04 , F02K1/60 , B64C15/04 , B63H11/10
CPC分类号： B64C25/423 , B64D33/04 , F02K1/60 , Y02T50/671
摘要： A thrust reversal system for an aircraft jet engine comprising a pair of thrust reverser doors constructed of a thin flexible material movable between a stowed and a deployed position and mechanism for moving same.
摘要翻译：一种用于飞机喷气式发动机的推力反转系统，包括一对推力反向器门，其由在可收起位置和展开位置之间移动的薄柔性材料构成，并且用于移动相对机构。

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