公开(公告)号：US20160333797A1

公开(公告)日：2016-11-17

申请号：US15090013

申请日：2016-04-04

Applicant: Bell Helicopter Textron Inc.

Inventor： Robert Michael Laramee ,  David L. Miller

IPC: F02C9/20 ,  F02C3/04 ,  B64D33/04 ,  F02C7/141

CPC classification number: B64D33/04 ,  B64D2033/045 ,  F02K1/825 ,  F05D2220/90

Abstract: An exhaust system has an engine exhaust plane associated with an entrance to the exhaust system, an exhaust exit plane associated with an exit of the exhaust system, a forward cap movable relative to the engine exhaust plane and configured to selectively intersect the engine exhaust plane, and an aft cap movable relative to the exhaust exit plane and configured to selectively intersect the exhaust exit plane.

Abstract translation: 排气系统具有与排气系统的入口相关联的发动机排气平面，与排气系统的出口相关联的排气出口平面，相对于发动机排气平面可移动并且构造成选择性地与发动机排气平面相交的前盖， 以及后盖，其能够相对于排气出口平面移动并且被配置为选择性地与排气出口平面相交。

公开(公告)号：US10457409B2

公开(公告)日：2019-10-29

申请号：US15090013

申请日：2016-04-04

Applicant: Bell Helicopter Textron Inc.

Inventor： Robert Michael Laramee ,  David L. Miller

IPC: B64D33/04 ,  F02K1/82

Abstract: An exhaust system has an engine exhaust plane associated with an entrance to the exhaust system, an exhaust exit plane associated with an exit of the exhaust system, a forward cap movable relative to the engine exhaust plane and configured to selectively intersect the engine exhaust plane, and an aft cap movable relative to the exhaust exit plane and configured to selectively intersect the exhaust exit plane.

公开(公告)号：US09927322B2

公开(公告)日：2018-03-27

申请号：US14254117

申请日：2014-04-16

Applicant: Bell Helicopter Textron Inc.

Inventor： Robert Michael Laramee ,  Carlos Fenny

IPC: G01M3/28 ,  B64D45/00 ,  G01F23/00 ,  G01F23/292 ,  G01F23/296 ,  G01M3/32 ,  G01F23/02

CPC classification number: G01M3/2853 ,  B64D45/00 ,  B64D2045/0085 ,  G01F23/0007 ,  G01F23/02 ,  G01F23/292 ,  G01F23/296 ,  G01F23/2966 ,  G01M3/2869 ,  G01M3/3245

Abstract: A rotorcraft actuator monitoring system to monitor leakage past dynamic rotorcraft actuator seals of a rotorcraft actuator includes a body member and a fluid level indication housing attached to the body member. The body member is mounted to surround a dynamic rotorcraft actuator seal that seals fluid in a rotorcraft actuator, where the body member captures fluid that leaks past the dynamic rotorcraft actuator seal. The fluid level indication housing collects the fluid captured by the body member and indicates that a predetermined volume of fluid that leaked past the dynamic rotorcraft actuator seal has been collected.

公开(公告)号：US20150300908A1

公开(公告)日：2015-10-22

申请号：US14254117

申请日：2014-04-16

Applicant: Bell Helicopter Textron Inc.

Inventor： Robert Michael Laramee ,  Carlos Fenny

IPC: G01M3/28 ,  G01F23/00 ,  B64D45/00

CPC classification number: G01M3/2853 ,  B64D45/00 ,  B64D2045/0085 ,  G01F23/0007 ,  G01F23/02 ,  G01F23/292 ,  G01F23/296 ,  G01F23/2966 ,  G01M3/2869 ,  G01M3/3245

Abstract: A rotorcraft actuator monitoring system to monitor leakage past dynamic rotorcraft actuator seals of a rotorcraft actuator includes a body member and a fluid level indication housing attached to the body member. The body member is mounted to surround a dynamic rotorcraft actuator seal that seals fluid in a rotorcraft actuator, where the body member captures fluid that leaks past the dynamic rotorcraft actuator seal. The fluid level indication housing collects the fluid captured by the body member and indicates that a predetermined volume of fluid that leaked past the dynamic rotorcraft actuator seal has been collected.

Abstract translation: 旋翼航空器致动器监控系统用于监测旋翼航空器致动器的动态旋翼航空器致动器密封件的泄漏，包括主体部件和连接到主体部件的液位指示壳体。 主体构件被安装成围绕动力旋翼航空器致动器密封件，其密封旋翼航空器致动器中的流体，其中主体构件捕获泄漏通过动态旋翼航空器致动器密封件的流体。 液面指示壳体收集由本体构件捕获的流体，并且指示已经收集经过动态旋翼航空器致动器密封件泄漏的预定体积的流体。