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公开(公告)号：US20160186598A1
公开(公告)日：2016-06-30
申请号：US14988815
申请日：2016-01-06
CPC分类号： F01D15/12 , F01D17/105 , F01D25/20 , F01D25/24 , F01D25/28 , F02C3/04 , F02C7/06 , F02C7/22 , F02C7/268 , F02C7/275 , F02C7/32 , F02C7/36 , F02K3/06 , F05D2220/32 , F05D2240/60 , F05D2260/4031 , F05D2260/85 , Y02T50/671
摘要： A nacelle for incorporation into a gas turbine engine has an inner wall defining a bypass duct, and an outer wall, at least one drive shaft extending through said inner wall, said at least one drive shaft to be connected to a gas turbine engine receiving the nacelle, said at least one drive shaft being connected to drive at least two accessory gear boxes, with said at least two accessory gear boxes being received between said inner and outer walls of said nacelle. A gas turbine engine is also disclosed.
摘要翻译： 用于结合到燃气涡轮发动机中的机舱具有限定旁通管道的内壁和外壁，延伸穿过所述内壁的至少一个驱动轴，所述至少一个驱动轴连接到燃气涡轮发动机， 所述至少一个驱动轴被连接以驱动至少两个附件齿轮箱，所述至少两个附件齿轮箱被容纳在所述机舱的所述内壁和外壁之间。 还公开了一种燃气涡轮发动机。
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2.发明申请Nacelle Anti-Ice Valve Utilized as Compressor Stability Bleed Valve During Starting 有权机舱防冰阀在起动期间用作压缩机稳定性排气阀公开(公告)号：US20140245749A1
公开(公告)日：2014-09-04
申请号：US13731133
申请日：2012-12-31
发明人： Claude Mercier , Gary Collopy
CPC分类号： F02C7/047 , B64D15/04 , B64D2033/0233 , F01D25/02 , F02C6/08 , F02C7/26 , F02C9/18 , F02C9/28 , F02C9/52 , F05D2270/101
摘要： A gas turbine engine has a compressor section received within an inner housing. An is an outer housing is spaced radially outwardly of the inner core housing. A nacelle has an anti-icing system which taps compressed air from the compressor section through an anti-ice valve and to the nacelle. The anti-ice valve is opened at startup of the gas turbine engine to assist compressor stability.
摘要翻译： 燃气涡轮发动机具有容纳在内壳体内的压缩机部分。 A是外壳体，其内径向内径向外延伸。 机舱具有防冰系统，其将来自压缩机部分的压缩空气通过防冰阀和机舱分接。 在燃气涡轮发动机起动时打开防冰阀，以帮助压缩机稳定。
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公开(公告)号：US09879599B2
公开(公告)日：2018-01-30
申请号：US13731133
申请日：2012-12-31
发明人： Claude Mercier , Gary Collopy
IPC分类号： F02C7/047 , F02C9/18 , F02C7/26 , F02C9/52 , F02C6/08 , B64D15/04 , F02C9/28 , F01D25/02 , B64D33/02
CPC分类号： F02C7/047 , B64D15/04 , B64D2033/0233 , F01D25/02 , F02C6/08 , F02C7/26 , F02C9/18 , F02C9/28 , F02C9/52 , F05D2270/101
摘要： A gas turbine engine has a compressor section received within an inner housing. An is an outer housing is spaced radially outwardly of the inner core housing. A nacelle has an anti-icing system which taps compressed air from the compressor section through an anti-ice valve and to the nacelle. The anti-ice valve is opened at startup of the gas turbine engine to assist compressor stability.
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4.发明申请LATCHING ACTUATION MECHANISM FOR NACELLE MOUNTED LATCHING SYSTEM 有权用于NACELLE MOUNTED LATCHING系统的锁紧机构公开(公告)号：US20150369083A1
公开(公告)日：2015-12-24
申请号：US14765424
申请日：2014-03-11
发明人： Claude Mercier
CPC分类号： F01D25/24 , B64D29/06 , F01D25/28 , F02K3/06 , F05D2230/72 , F05D2240/14
摘要： An assembly for a gas turbine engine includes a first fan cowl pivotable on a hinge from a first position to a second position. A latching actuation mechanism is disposed under the nacelle, engages the hinge, and is actuated by movement of the hinge between the first position and the second position.
摘要翻译： 用于燃气涡轮发动机的组件包括可在铰链上从第一位置枢转到第二位置的第一风扇罩。 闩锁致动机构设置在机舱的下方，与铰链接合，并且通过铰链在第一位置和第二位置之间的移动而被致动。
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公开(公告)号：US20150274307A1
公开(公告)日：2015-10-01
申请号：US14737617
申请日：2015-06-12
发明人： Claude Mercier , Thomas G. Cloft
CPC分类号： F01D25/24 , B64C7/02 , B64D29/06 , F01D11/005 , F02K3/06 , F05D2230/72 , F05D2240/14 , F05D2260/30
摘要： A latch assembly for securing a nacelle portion of a gas turbine engine includes an engine case structure that includes a core compartment. An inner flow structure has closed and opened positions with respect to the engine case structure. The inner flow structure encloses the core compartment in the closed position and provides access to the core compartment in the opened position. A bypass flowpath is provided by a portion of the engine case structure and the inner flow structure. A seal is engaged with the engine case structure and the inner flow structure in the closed position. A latch has a latched position in which radial movement of the inner flow structure relative to the engine case structure is impeded and maintained in the closed position and an unlatched position in which the inner flow structure is permitted to move radially outward to the opened position.
摘要翻译： 用于固定燃气涡轮发动机的机舱部分的闩锁组件包括包括芯室的发动机壳体结构。 内部流动结构相对于发动机壳体结构具有闭合和打开的位置。 内部流动结构将核心隔间封闭在关闭位置，并提供到处于打开位置的核心隔间的通路。 旁路流路由发动机外壳结构和内流结构的一部分提供。 密封件与发动机壳体结构和内部流动结构接合在关闭位置。 闩锁具有锁定位置，其中内部流动结构相对于发动机壳体结构的径向运动被阻碍并保持在关闭位置和允许内部流动结构径向向外移动到打开位置的解锁位置。
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公开(公告)号：US09297314B2
公开(公告)日：2016-03-29
申请号：US13719303
申请日：2012-12-19
CPC分类号： F01D15/12 , F01D17/105 , F01D25/20 , F01D25/24 , F01D25/28 , F02C3/04 , F02C7/06 , F02C7/22 , F02C7/268 , F02C7/275 , F02C7/32 , F02C7/36 , F02K3/06 , F05D2220/32 , F05D2240/60 , F05D2260/4031 , F05D2260/85 , Y02T50/671
摘要： A nacelle for incorporation into a gas turbine engine has an inner wall defining a bypass duct, and an outer wall. At least one drive shaft extends through the inner wall. The at least one drive shaft is connected to a gas turbine engine receiving the nacelle. The at least one drive shaft is connected to drive at least two accessory gear boxes, with the at least two accessory gear boxes being received between the inner and outer walls of the nacelle. A gas turbine engine is also disclosed.
摘要翻译： 用于并入燃气涡轮发动机的机舱具有限定旁通管道的内壁和外壁。 至少一个驱动轴延伸穿过内壁。 所述至少一个驱动轴连接到接收所述机舱的燃气涡轮发动机。 所述至少一个驱动轴被连接以驱动至少两个附件齿轮箱，所述至少两个附件齿轮箱被容纳在所述机舱的内壁和外壁之间。 还公开了一种燃气涡轮发动机。
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公开(公告)号：US20160010561A1
公开(公告)日：2016-01-14
申请号：US14764105
申请日：2013-01-30
CPC分类号： F02C7/32 , B64D29/06 , F02C3/04 , F05D2250/313 , F05D2250/75
摘要： An example gas turbine engine includes, among other things, a nacelle having an inner wall providing a bypass duct of a gas turbine engine, and an outer wall; an accessory gearbox is received between the inner wall and the outer wall of the nacelle; and an accessory drive of the accessory gearbox is configured to rotate about an accessory drive axis that is transverse to a central axis of the gas turbine engine.
摘要翻译： 一个示例性的燃气涡轮发动机包括其中具有提供燃气涡轮发动机的旁路管道的内壁的机舱和外壁; 附件齿轮箱被容纳在机舱的内壁和外壁之间; 并且附件齿轮箱的附件驱动器被配置为围绕横向于燃气涡轮发动机的中心轴线的附件驱动轴线旋转。
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公开(公告)号：US20150251774A1
公开(公告)日：2015-09-10
申请号：US14202688
申请日：2014-03-10
发明人： Claude Mercier
CPC分类号： B64D27/26 , B64F5/50 , F01D25/285 , Y10T29/53961
摘要： An engine installation system includes two aftward members and two forward members. Each member is connected to a different bootstrap on one end and has a pivotable connection to a pylon on the other end. There is a link that connects one forward member with one aftward member, and another link that connects the other forward member with the other aftward member. There is a variable-length member connected to the bootstrap-end of each of the two aftward members, with each of the variable-length members having a pivotable connection to the pylon.
摘要翻译： 发动机安装系统包括两个后部构件和两个前进构件。 每个构件在一端连接到不同的引导件，并且具有与另一端的托架的可枢转连接。 有一个连接，一个前向构件与一个后退构件连接，另一个连接将另一个前部构件与另一个后部构件连接。 连接到两个后部构件中的每一个的自举端的可变长度构件，其中每个可变长度构件具有到塔的可枢转连接。
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公开(公告)号：US20140075918A1
公开(公告)日：2014-03-20
申请号：US13622450
申请日：2012-09-19
发明人： Claude Mercier , Thomas G. Cloft
CPC分类号： F02K3/06 , B64D29/00 , B64D29/08 , F01D25/24 , F01D25/243 , F01D25/28 , F01D25/285 , F02C7/04 , F02C7/32 , F02K1/766 , F02K1/80 , F05D2230/72 , F05D2240/14 , F05D2260/30
摘要： A nacelle structure for a gas turbine engine includes an outer nacelle surrounding a fan section and defining an outer boundary of a bypass flow passage and an inner nacelle surrounding a core engine section and defining an inner boundary of the bypass flow passage. A panel of the inner nacelle is moveable between an open position providing access to the core engine section and a closed position. A lock is supported within the inner nacelle proximate the panel. The lock includes an electric actuator for moving a locking pin between a locked position and an unlocked position. The lock prevents opening and limits deflection of the panel when in the locked position.
摘要翻译： 用于燃气涡轮发动机的机舱结构包括围绕风扇部分并限定旁路流动通道的外部边界的外部机舱和围绕核心发动机部分并限定旁路流动通道的内部边界的内部机舱。 内部机舱的面板可以在提供通向核心发动机部分的打开位置和关闭位置之间移动。 在靠近面板的内部机舱中支撑锁。 该锁包括用于在锁定位置和解锁位置之间移动锁定销的电致动器。 当锁定位置时，该锁可防止打开并限制面板的偏转。
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公开(公告)号：US10145335B2
公开(公告)日：2018-12-04
申请号：US13712240
申请日：2012-12-12
摘要： An example thrust reverser of a gas turbine engine is configured to connect to an aircraft wing via a pylon via one or more thrust reverser mounts located adjacent to a top circumferential apex of the engine according to an exemplary aspect of the present disclosure includes, among other things, a first cowl moveable between a stowed position and a deployed position relative to a second cowl. The first cowl in the deployed position configured to permit thrust to be redirected from an engine to slow the engine. The first cowl forming a portion of a substantially annular encasement of the engine. The first cowl directly interfaces with second cowl of the encasement at a cowl interface position that is more than 18 degrees circumferentially offset from the top circumferential apex when the first cowl is in the stowed position.
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