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1. 发明申请

WO2014197057A2 CASTELLATED LATCH MECHANISM FOR A GAS TURBINE ENGINE 审中-公开
标题翻译：用于气体涡轮发动机的机舱锁紧机构
公开(公告)号：WO2014197057A2
公开(公告)日：2014-12-11
申请号：PCT/US2014/025191
申请日：2014-03-13
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： SAWYERS-ABBOTT, Nigel David
IPC分类号： F02C7/20 , F01D25/28
CPC分类号： F01D25/265 , B64D29/06 , B64D29/08 , F01D15/10 , F01D25/246 , F01D25/28 , F02C3/04 , F02C7/20 , F02K1/72 , F02K1/80 , F02K1/805 , F05D2220/32 , F05D2250/182 , F05D2250/71 , F05D2260/36
摘要： A gas turbine engine includes a fan duct including a fan duct inner structure that surrounds a core engine, a fan case that surrounds a fan, a core engine frame, and at least one mechanism configured to secure a portion of the fan duct inner structure to a portion of the core engine frame. The at least one mechanism includes a castellated arcuate portion mounted to one of the fan duct inner structure and the core engine frame and an inwardly projecting retaining feature mounted to the other of the fan duct inner structure and the core engine frame. The castellated arcuate portion is rotatable about an engine central longitudinal axis to position a feature of the castellated arcuate portion proximate to a portion of the inwardly projecting retaining feature to latch the fan duct inner structure.
摘要翻译：燃气涡轮发动机包括风扇管道，风扇管道包括围绕发动机的风扇管道内部结构，围绕风扇的风扇壳体，核心发动机框架，以及至少一个机构，其构造成将风扇管道内部结构的一部分固定到核心引擎框架的一部分。所述至少一个机构包括安装到所述风扇管道内部结构和所述核心发动机框架中的一个的雉形弧形部分，以及安装到所述风扇管道内部结构和所述核心引擎框架中的另一个的向内突出的保持特征。雉形弧形部分可围绕发动机中心纵向轴线旋转，以将cast形弧形部分的特征定位成靠近向内突出的保持特征的一部分，以锁住风扇管道内部结构。

2. 发明申请

WO2014133770A1 GAS TURBINE ENGINE NOISE REDUCING NOSE CONE 审中-公开
标题翻译：气体涡轮发动机噪音减少噪声
公开(公告)号：WO2014133770A1
公开(公告)日：2014-09-04
申请号：PCT/US2014/016196
申请日：2014-02-13
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： GILSON, Jonathan , SAWYERS-ABBOTT, Nigel David
IPC分类号： F02C7/045 , F02C7/04 , F01D25/00
CPC分类号： F02C7/045 , F01D5/02 , F01D25/24 , F05D2220/32 , F05D2220/36 , F05D2260/963
摘要： A fan section for a gas turbine engine includes a fan hub and a nose cone section operatively mounted to the fan hub. The nose cone section includes a noise attenuation feature.
摘要翻译：用于燃气涡轮发动机的风扇部分包括可操作地安装到风扇轮毂的风扇轮毂和鼻锥部分。鼻锥部分包括噪声衰减特征。

3. 发明申请

WO2014172016A3 PIVOT DOOR THRUST REVERSER WITH VARIABLE AREA NOZZLE 审中-公开
标题翻译： PIVOT门推出带可变面积喷嘴的换向器
公开(公告)号：WO2014172016A3
公开(公告)日：2014-10-23
申请号：PCT/US2014/018825
申请日：2014-02-27
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： SAWYERS-ABBOTT, Nigel David , LOFFREDO, Constantino V.
IPC分类号： F02K3/02 , F02K1/06 , F02K1/10 , F02K1/15
摘要： 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.
摘要翻译：燃气涡轮发动机包括机舱组件，该机舱组件具有围绕发动机轴线限定的核心机舱以及至少部分地安装在核心机舱周围以限定风扇旁路流动路径的风扇外罩组件。风扇外罩组件包括风扇风道外罩部分和相对于风扇风道外罩部分可移动的风扇喷嘴外罩部分。推力反向器系统包括多个枢转门，枢转门相对于风扇外罩组件在收起位置和展开位置之间可移动。可变面积风扇喷嘴与风扇旁路流动路径连通。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。

4. 发明申请

WO2014197033A2 PIVOT DOOR THRUST REVERSER 审中-公开
标题翻译： PIVOT门扭矩反转器
公开(公告)号：WO2014197033A2
公开(公告)日：2014-12-11
申请号：PCT/US2014/022955
申请日：2014-03-11
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： SAWYERS-ABBOTT, Nigel David
IPC分类号： F02K1/74 , F02K1/76 , F02K3/06 , B64D29/06 , B64D33/04 , B64C9/32
CPC分类号： F02K1/72 , B64D29/06 , B64D33/04 , F01D5/02 , F01D15/12 , F01D17/105 , F01D25/24 , F02K1/70 , F05D2220/36 , F05D2260/40311
摘要： A geared turbofan engine includes a fan, a low pressure turbine, a geared architecture, and a nacelle. The fan and low pressure turbine are capable of rotation about an axial centerline of the gas turbine engine. The geared architecture connects the fan to be driven by the low pressure turbine. The nacelle is disposed circumferentially around the fan and defines a portion of a bypass flow duct. The nacelle includes a thrust reverser assembly with one or more doors that pivot to block at least a portion of the bypass flow duct in a deployed position.
摘要翻译：齿轮涡扇发动机包括风扇，低压涡轮机，齿轮架构和机舱。风扇和低压涡轮机能够围绕燃气涡轮发动机的轴向中心线旋转。齿轮架构将风扇连接到低压涡轮机驱动。机舱围绕风扇周向设置并限定旁路流动管道的一部分。机舱包括具有一个或多个门的推力反向器组件，其枢转以在展开位置阻挡旁路流动管道的至少一部分。

5. 发明申请

WO2014164238A1 GAS TURBINE ENGINE HYDRAULICALLY OPERATED NACELLE LATCH 审中-公开
标题翻译：气体涡轮发动机液压操作的NACELLE LATCH
公开(公告)号：WO2014164238A1
公开(公告)日：2014-10-09
申请号：PCT/US2014/021477
申请日：2014-03-07
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： SAWYERS-ABBOTT, Nigel David
IPC分类号： B64D33/02 , F02C7/04
CPC分类号： F01D25/28 , B64D29/06 , F01D25/24 , F02C3/04 , F02C7/00 , F02K1/763 , F05D2260/30 , F05D2260/406
摘要： A method of actuating a hydraulic latch and a fan duct includes providing a pressurized fluid for actuating a latch, providing a valve to control flow of pressurized fluid to the latch and the fan duct, and selectively opening the valve, whereby the pressurized fluid opens the fan duct. A gas turbine engine includes a fan duct with an inner structure surrounding an engine core, a fan case surrounding a fan, and at least one latch. The at least one latch secures a first portion of the fan duct inner structure to a core engine fame or to a second portion of the fan duct inner structure. The at least one latch is also configured to secure the second portion of the fan duct inner structure to the core engine fame or to the first portion of the fan duct inner structure.
摘要翻译：致动液压闩锁和风扇管道的方法包括提供用于致动闩锁的加压流体，提供阀门以控制加压流体到闩锁和风扇管道的流动，并且选择性地打开阀门，由此加压流体打开风机管道。燃气涡轮发动机包括具有围绕发动机芯的内部结构的风扇管道，围绕风扇的风扇壳体和至少一个闩锁件。至少一个闩锁将风扇管道内部结构的第一部分固定到核心发动机机构或风扇管道内部结构的第二部分。至少一个闩锁还被构造成将风扇管道内部结构的第二部分固定到核心引擎名誉或者将风扇管道内部结构的第一部分固定。

6. 发明申请

WO2014151275A1 NACELLE MOUNTED LATCHING SYSTEM 审中-公开
标题翻译： NACELLE安装式锁定系统
公开(公告)号：WO2014151275A1
公开(公告)日：2014-09-25
申请号：PCT/US2014/025335
申请日：2014-03-13
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： SAWYERS-ABBOTT, Nigel David , FOSTER, Joseph P.
IPC分类号： B64D33/02 , F02C7/04
CPC分类号： F01D25/265 , B64D29/06 , F01D21/00 , F02C7/20 , F02K1/32 , F05D2220/32 , F05D2260/30
摘要： A nacelle for a gas turbine engine includes a upper and lower bifurcations, an inner diameter cowl and a first latch system. The inner diameter cowl extends between the upper and lower bifurcations and the first latch system is mounted on the inner diameter cowl. The first latch system is spaced along the inner diameter cowl between the upper and lower bifurcations.
摘要翻译：用于燃气涡轮发动机的机舱包括上部和下部分叉，内径整流罩和第一闩锁系统。内径整流罩在上下分叉之间延伸，第一闩锁系统安装在内径整流罩上。第一闩锁系统沿着上下分叉之间的内径罩分开。

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