公开(公告)号：US10400621B2

公开(公告)日：2019-09-03

申请号：US14765037

申请日：2014-02-27

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Nigel David Sawyers-Abbott ,  Constantino V. Loffredo

IPC: F02K1/09 ,  F02K1/70 ,  F02K1/72 ,  F01D17/14 ,  F02K1/12 ,  F01D9/04 ,  F01D25/24 ,  F02K1/15 ,  F02K1/76 ,  F02K3/075

Abstract: A gas turbine engine includes a nacelle assembly having a core nacelle defined about an engine axis and a fan nacelle assembly mounted at least partially around the core nacelle to define a fan bypass flow path. The fan nacelle assembly includes a fan duct nacelle section and a fan nozzle nacelle section moveable relative to the fan duct nacelle section. A thrust reverser system includes a plurality of pivot doors movable relative to the fan nacelle assembly between stowed and deployed positions. A variable area fan nozzle is in communication with the fan bypass flow path. A first actuator is mounted to the fan duct nacelle section to actuate the pivot door thrust reverser system, and a second actuator is mounted to the fan duct nacelle section to move the fan nozzle nacelle section relative to the fan duct nacelle section to vary a fan nozzle exit area.

公开(公告)号：US20150369078A1

公开(公告)日：2015-12-24

申请号：US14765037

申请日：2014-02-27

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Nigel David Sawyers-Abbott ,  Constantino V. Loffredo

IPC: F01D17/14 ,  F01D9/04 ,  F01D25/24 ,  F02K1/15 ,  F02K1/76

CPC classification number: F01D17/14 ,  F01D9/04 ,  F01D25/24 ,  F02K1/09 ,  F02K1/1261 ,  F02K1/15 ,  F02K1/70 ,  F02K1/72 ,  F02K1/763 ,  F02K3/075 ,  F05D2220/32 ,  F05D2270/62 ,  F05D2270/64 ,  F05D2270/65

Abstract: A gas turbine engine includes a nacelle assembly having a core nacelle defined about an engine axis and a fan nacelle assembly mounted at least partially around the core nacelle to define a fan bypass flow path. The fan nacelle assembly includes a fan duct nacelle section and a fan nozzle nacelle section moveable relative to the fan duct nacelle section. A thrust reverser system includes a plurality of pivot doors movable relative to the fan nacelle assembly between stowed and deployed positions. A variable area fan nozzle is in communication with the fan bypass flow path. A first actuator is mounted to the fan duct nacelle section to actuate the pivot door thrust reverser system, and a second actuator is mounted to the fan duct nacelle section to move the fan nozzle nacelle section relative to the fan duct nacelle section to vary a fan nozzle exit area.

Abstract translation: 燃气涡轮发动机包括具有围绕发动机轴线限定的核心机舱的机舱组件和至少部分地安装在核心机舱周围的风扇机舱组件，以限定风扇旁路流动路径。 风扇机舱组件包括风扇管道机舱部分和相对于风扇管道机舱部分可移动的风扇喷嘴机舱部分。 推力反向器系统包括在收起和展开位置之间可相对于风扇机舱组件移动的多个枢轴门。 可变区域风扇喷嘴与风扇旁路流路连通。 第一致动器安装到风扇管道机舱部分以致动枢转门推力反向器系统，并且第二致动器安装到风扇管道机舱部分以相对于风扇管道机舱部分移动风扇喷嘴机舱部分以改变风扇 喷嘴出口区域。