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1. 发明申请

WO2014028078A3 A GAS TURBINE ENGINE AND NACELLE NOISE ATTENUATION STRUCTURE 审中-公开
标题翻译：燃气涡轮发动机与纳机噪声衰减结构
公开(公告)号：WO2014028078A3
公开(公告)日：2014-04-10
申请号：PCT/US2013037686
申请日：2013-04-23
申请人： UNITED TECHNOLOGIES CORP
发明人： GILSON JONATHAN , MAY MOLLY M , WELCH DAVID A , SAWYERS-ABBOTT NIGEL DAVID
IPC分类号： F02C7/045 , F02K1/34
CPC分类号： F02C3/04 , F02C3/107 , F02C7/045 , F02K3/06 , F04D29/545 , F04D29/644 , F04D29/664
摘要： A nacelle structure for a gas turbine engine assembly includes a fan case, and inlet, and a noise attenuation device. The fan case is configured to be disposed about a fan section of the gas turbine engine, which fan section has a diameter D. The inlet is attached to the fan case and extends axially forward of the fan case. A hilite of the inlet is spaced a distance L from a region in which the fan section is configured to be disposed. A ratio L/D is less than about 0.6. The noise attenuation structure covers a portion of an inner surface of the fan case and the inlet.
摘要翻译：用于燃气涡轮发动机组件的机舱结构包括风扇壳体和入口以及噪声衰减装置。风扇外壳被配置为围绕燃气涡轮发动机的风扇部分设置，该风扇部分具有直径D.入口连接到风扇外壳并且在风扇外壳的轴向前方延伸。入口的hilite与配置有风扇部分的区域间隔距离L. 比值L / D小于约0.6。噪声衰减结构覆盖风扇外壳的内表面和入口的一部分。

2. 发明申请

WO2014197033A3 PIVOT DOOR THRUST REVERSER 审中-公开
标题翻译： PIVOT门扭矩反转器
公开(公告)号：WO2014197033A3
公开(公告)日：2015-02-05
申请号：PCT/US2014022955
申请日：2014-03-11
申请人： UNITED TECHNOLOGIES CORP
发明人： SAWYERS-ABBOTT NIGEL DAVID
IPC分类号： F02K1/74 , B64C9/32 , B64D29/06 , B64D33/04 , F02K1/76 , F02K3/06
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。

3. 发明申请

WO2014197057A3 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：WO2014197057A3
公开(公告)日：2015-02-19
申请号：PCT/US2014025191
申请日：2014-03-13
申请人： UNITED TECHNOLOGIES CORP
发明人： SAWYERS-ABBOTT NIGEL DAVID
IPC分类号： F02C7/20 , F01D25/28
CPC分类号： F01D25/265 , F01D15/10 , F01D25/246 , F01D25/28 , F02C3/04 , F02C7/20 , F02K1/72 , 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。

4. 发明申请

WO2014172016A2 PIVOT DOOR THRUST REVERSER WITH VARIABLE AREA NOZZLE 审中-公开
标题翻译： PIVOT门扭转逆变器与可变区域喷嘴
公开(公告)号：WO2014172016A2
公开(公告)日：2014-10-23
申请号：PCT/US2014018825
申请日：2014-02-27
申请人： UNITED TECHNOLOGIES CORP
发明人： SAWYERS-ABBOTT NIGEL DAVID , LOFFREDO CONSTANTINO V
CPC分类号： F01D17/14 , F01D9/04 , F01D25/24 , F02K1/09 , F02K1/1261 , F02K1/15 , F02K1/70 , F02K1/763 , F02K3/075 , F05D2220/32 , F05D2270/62 , F05D2270/64 , F05D2270/65
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。

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