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1. 发明申请

WO2014052558A1 GEARED TURBOFAN WITH FAN AND CORE MOUNTED ACCESSORY GEARBOXES 审中-公开
标题翻译：具有风扇和核心安装附件齿轮的齿轮涡轮机
公开(公告)号：WO2014052558A1
公开(公告)日：2014-04-03
申请号：PCT/US2013/061872
申请日：2013-09-26
申请人： UNITED TECHNOLOGIES CORPORATION , CLOFT, Thomas G. , GUKEISEN, Robert L. , MERCIER, Claude
发明人： CLOFT, Thomas G. , GUKEISEN, Robert L. , MERCIER, Claude
IPC分类号： F02C7/36 , F02C7/00 , F01D25/00
CPC分类号： F02C7/32 , F02C3/107 , F02C7/36 , F02K3/06 , F05D2240/40 , F05D2250/36 , F05D2260/4031 , F05D2260/40311
摘要： A disclosed accessory drive system provides for the reduction in the overall diameter of the outer nacelle by splitting the number of accessory components between a first gear box mounted within the outer nacelle and a second gearbox mounted to the core engine. The first gear box mounted to the fan case of the gas turbine engine drives a first plurality of accessory components. The second gear box mounted to a core engine case of the gas turbine engine drives a second plurality of accessory components.
摘要翻译：所公开的附件驱动系统通过将安装在外舱内的第一齿轮箱和安装到核心发动机的第二齿轮箱之间的分配多个附件组件来提供外舱的整体直径的减小。安装在燃气涡轮发动机的风扇壳体上的第一齿轮箱驱动第一多个辅助部件。安装到燃气涡轮发动机的核心发动机壳体的第二齿轮箱驱动第二多个附件部件。

2. 发明申请

WO2008045062A1 FAN VARIABLE AREA NOZZLE FOR A GAS TURBINE ENGINE FAN NACELLE WITH SLIDING ACTUATION SYSTEM 审中-公开
标题翻译：风力发动机风扇风扇风扇风扇系统
公开(公告)号：WO2008045062A1
公开(公告)日：2008-04-17
申请号：PCT/US2006/039936
申请日：2006-10-12
申请人： UNITED TECHNOLOGIES CORPORATION , GUKEISEN, Robert L.
发明人： GUKEISEN, Robert L.
IPC分类号： F02K1/12 , F02K3/06
CPC分类号： F02K1/1261 , F02K1/12 , F02K1/1253 , F02K3/06 , F02K3/075 , F05D2260/50
摘要： A fan variable area nozzle (FVAN) includes a flap assembly which varies a fan nozzle exit area. An actuator system drives a sliding drive ring relative a multitude of slider tracks mounted to a fan nacelle to adjust each flap of the flap assembly through the flap linkage to pitch the flap assembly about a circumferential hinge line to vary the diameter of the annular fan nozzle exit area between the fan nacelle and the core nacelle. The FVAN may be separated into a multiple of drive ring sectors which are each independently adjustable by an associated actuator of the actuator system to provide a low profile drag asymmetrical fan nozzle exit area.
摘要翻译：风扇可变面积喷嘴（FVAN）包括改变风扇喷嘴出口区域的翼片组件。致动器系统相对于安装到风扇机舱的多个滑动轨道驱动滑动驱动环，以通过翼片连杆调整翼片组件的每个翼片，以围绕圆周铰链线对翼片组件进行间距以改变环形风扇喷嘴的直径风扇机舱和核心机舱之间的出口区域。 FVAN可以分成多个驱动环段，每个驱动环扇区可由致动器系统的相关联的致动器独立地调节，以提供低轮廓阻力不对称的风扇喷嘴出口区域。

3. 发明申请

WO2014046713A1 GEARED GAS TURBINE ENGINE ACCESSORY GEARBOX 审中-公开
标题翻译：齿轮式涡轮发动机附件齿轮箱
公开(公告)号：WO2014046713A1
公开(公告)日：2014-03-27
申请号：PCT/US2013/022370
申请日：2013-01-21
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： CLOFT, Thomas G. , GUKEISEN, Robert L.
IPC分类号： F02C7/32 , B64D41/00
CPC分类号： F02C7/32 , F01D15/10 , F01D15/12 , F05D2220/76 , F05D2260/4031 , F05D2260/53
摘要： A gas turbine engine includes a gearbox. The gearbox includes a housing at a forward part of a core compartment of a gas turbine engine. A plurality of accessory drives are each configured to rotatably couple the gas turbine engine accessory gearbox to one of a plurality of accessory components.
摘要翻译：燃气涡轮发动机包括齿轮箱。齿轮箱包括在燃气涡轮发动机的核心舱的前部的壳体。多个附件驱动器各自构造成将燃气涡轮发动机附件齿轮箱可旋转地联接到多个附件部件中的一个。

4. 发明申请

WO2014052061A1 TURBOMACHINE THRUST REVERSER 审中-公开
公开(公告)号：WO2014052061A1
公开(公告)日：2014-04-03
申请号：PCT/US2013/059878
申请日：2013-09-16
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： GUKEISEN, Robert L. , MERCIER, Claude , MALECKI, Robert E.
IPC分类号： F02K1/62 , B64D33/04
CPC分类号： F02K1/58 , B64D29/06 , F02C7/20 , F02K1/64 , F05D2250/34
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.
摘要翻译：燃气涡轮发动机的示例推力反向器被构造成根据本公开的示例性方面经由经由一个或多个相对于发动机的顶部圆周顶点定位的一个或多个推力反向器安装座经由塔架连接到飞机机翼，事物，第一整流罩可相对于第二整流罩在收起位置和展开位置之间移动。在展开位置的第一个整流罩配置成允许从发动机重新引导推力以减慢发动机。第一整流罩形成发动机的大致环形的壳体的一部分。当第一整流罩处于收起位置时，第一整流罩直接与外壳的第二整流罩接合在整流罩接口位置，该顶盖接口位置与顶部圆周顶点周向偏移大于18度。

5. 发明申请

WO2014055103A1 PYLON SHAPE WITH GEARED TURBOFAN FOR STRUCTURAL STIFFNESS 审中-公开
标题翻译：具有结构强度的齿轮形涡轮的PYLON形状
公开(公告)号：WO2014055103A1
公开(公告)日：2014-04-10
申请号：PCT/US2013/025717
申请日：2013-02-12
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： GUKEISEN, Robert L.
IPC分类号： F02C7/20 , B64D27/12 , F02K3/06 , F02C7/00
CPC分类号： B64D27/12 , B64D27/18 , B64D27/26 , B64D2027/266 , F02C7/20 , F02K3/06 , F05D2260/40311 , Y02T50/44
摘要： A gas turbine includes a mounting structure for mounting the engine to a pylon. A propulsor section includes a fan having a fan diameter. A geared architecture drives the fan. A generator section includes a fan drive turbine that drives the geared architecture. A turbine to fan diameter ratio is substantially less than 45%.
摘要翻译：燃气轮机包括用于将发动机安装到塔架的安装结构。推进器部分包括具有风扇直径的风扇。齿轮架构驱动风扇。发电机部分包括驱动齿轮架构的风扇驱动涡轮机。涡轮风扇直径比大体上小于45％。

6. 发明申请

WO2014120134A1 GAS TURBINE ENGINE ACCESSORY GEARBOX 审中-公开
标题翻译：燃气涡轮发动机配件齿轮箱
公开(公告)号：WO2014120134A1
公开(公告)日：2014-08-07
申请号：PCT/US2013/023713
申请日：2013-01-30
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： CLOFT, Thomas G. , GUKEISEN, Robert L. , MERCIER, Claude
IPC分类号： F01D15/12
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通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。

7. 发明申请

WO2014099890A1 GAS TURBINE ENGINE WITH ACCESSORY GEAR BOX 审中-公开
标题翻译：具有附件齿轮箱的气体涡轮发动机
公开(公告)号：WO2014099890A1
公开(公告)日：2014-06-26
申请号：PCT/US2013/075626
申请日：2013-12-17
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： CLOFT, Thomas G. , GUKEISEN, Robert L. , MERCIER, Claude
IPC分类号： F02C7/36 , F01D15/12
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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