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1. 发明申请

WO2014130361A1 TURBOFAN ENGINE INCLUDING THIRD FLOWPATH EXHAUST NOZZLE 审中-公开
标题翻译：涡轮发动机，包括第三个流量排气喷嘴
公开(公告)号：WO2014130361A1
公开(公告)日：2014-08-28
申请号：PCT/US2014/016509
申请日：2014-02-14
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： ROBERGE, Gary D.
IPC分类号： F02K1/12 , F02K1/38 , F02K3/02 , F01D17/14
CPC分类号： F02K1/1207 , F02K1/008 , F02K1/1292 , F02K1/38 , F02K3/02 , F02K3/075 , F02K3/077 , F05D2240/128 , F05D2250/36
摘要： A turbofan engine that includes a first flowpath, a second flowpath, a third flowpath, and a third flowpath exhaust nozzle is provided. The first flowpath is radially inboard of the second flowpath at a location upstream of a core section of the turbofan engine. The third flowpath is radially outboard of the second flowpath at the location upstream of the core section. The third flowpath exhaust nozzle defines a plurality of third flowpath exhaust exit ports through which gas traveling along the third flowpath may be discharged. An area or a geometry of each of the plurality of third flowpath exhaust exit ports is independently and selectively adjustable. A method for operating the turbofan engine includes independently and selectively adjusting an area or a geometry of at least one of the plurality of third flowpath exhaust exit ports to achieve a desired engine operation.
摘要翻译：提供了包括第一流路，第二流路，第三流路和第三流路排气喷嘴的涡轮风扇发动机。第一流路在涡轮风扇发动机的核心部分的上游的位置处径向地位于第二流动路径的内侧。第三流路径位于第二流路径的外侧，位于核心部分的上游位置处。第三流路排气喷嘴限定了多个第三流路排气出口，通过该排出口可以排出沿第三流路行进的气体。多个第三流路排出口中的每一个的区域或几何形状是可独立且有选择地调节的。用于操作涡扇风扇发动机的方法包括独立地和选择性地调节多个第三流路排气出口中的至少一个的面积或几何形状，以实现期望的发动机操作。

2. 发明申请

WO2014123841A1 REMOVABLE FILM FOR AIRFOIL SURFACES 审中-公开
标题翻译：用于气垫表面的可拆卸膜
公开(公告)号：WO2014123841A1
公开(公告)日：2014-08-14
申请号：PCT/US2014/014556
申请日：2014-02-04
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： ROBERGE, Gary D.
IPC分类号： F01D5/14 , F01D9/02 , F02C7/00
CPC分类号： F01D5/288 , B64D15/00 , B64D2045/009 , F01D5/02 , F01D9/041 , F01D17/14 , F01D25/005 , F01D25/02 , F01D25/24 , F02C3/04 , F05D2220/32 , F05D2220/36 , F05D2230/70 , F05D2230/80 , F05D2230/90 , F05D2300/512 , Y02T50/673
摘要： A fan section to be incorporated into a gas turbine engine has a rotor and a plurality of fan blades. The fan blades deliver air into a bypass duct defined inwardly of the nacelle and into a core engine. There are static vanes inward of the nacelle. A surface of the fan section is provided with a removable film material. A gas turbine engine and a method of refurbishing a surface are also disclosed.
摘要翻译：并入燃气轮机的风扇部分具有转子和多个风扇叶片。风扇叶片将空气输送到定位在机舱内部并进入核心发动机的旁路管道中。机舱内有静叶片。风扇部分的表面设置有可移除的膜材料。还公开了一种燃气涡轮发动机和一种翻新表面的方法。

3. 发明申请

WO2013172899A2 GAS TURBINE ENGINE SYSTEMS INVOLVING TIP FANS 审中-公开
标题翻译：涉及风机的气体涡轮发动机系统
公开(公告)号：WO2013172899A2
公开(公告)日：2013-11-21
申请号：PCT/US2013/026903
申请日：2013-02-20
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： ROBERGE, Gary D. , SUCIU, Gabriel L.
IPC分类号： F02K3/065 , F02K3/072 , F02C7/00
CPC分类号： F02K3/077 , F02C7/36 , F02K3/072 , F05D2260/40311
摘要： Gas turbine engine systems involving tip fans are provided. In this regard, a representative gas turbine engine system includes: a multi-stage fan having a first rotatable set of blades and a second counter-rotatable set of blades, the second rotatable set of blades defining an inner fan and a tip fan and being located downstream of the first set of rotatable blades; and an epicyclic differential gear assembly operative to receive a torque input and differentially apply the torque input to the first set of blades and the second set of blades.
摘要翻译：提供了涉及尖端风扇的燃气涡轮发动机系统。在这方面，代表性的燃气涡轮发动机系统包括：多级风扇，具有第一可转动的叶片组和第二可反向旋转的叶片组，第二可旋转叶片限定内部风扇和顶端风扇，位于第一组可旋转叶片的下游; 以及行星差速齿轮组件，其操作以接收扭矩输入并且差分地施加到第一组叶片和第二组叶片的扭矩输入。

4. 发明申请

WO2015108592A2 MULTI-MATERIAL TURBINE AIRFOIL 审中-公开
标题翻译：多材料涡轮机空气
公开(公告)号：WO2015108592A2
公开(公告)日：2015-07-23
申请号：PCT/US2014/061916
申请日：2014-10-23
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： ROBERGE, Gary D.
IPC分类号： F01D5/14 , F01D5/28
CPC分类号： F01D5/282 , B23P15/04 , F01D5/147 , F01D5/18 , F01D5/284 , F01D9/041 , F01D25/005 , F01D25/12 , F04D29/321 , F05D2220/32 , F05D2240/303 , F05D2260/36 , F05D2300/5023 , F05D2300/522 , Y02T50/672
摘要： A turbine component comprises a platform and an airfoil extending radially away from the platform and extending from a leading edge to a trailing edge. A leading edge portion defines the leading edge of the airfoil and a trailing edge portion including the trailing edge. One of the leading and trailing edge portions also includes the platform. The leading edge portion is formed of a first material distinct from a second material forming the trailing edge portion. The first material has an operating temperature capability at least 100F higher than that of the second material. A gas turbine engine is also disclosed.
摘要翻译：涡轮机部件包括平台和从平台径向延伸并从前缘延伸到后缘的翼型件。前缘部分限定翼型件的前缘和包括后缘的后缘部分。前缘部分和后缘部分之一也包括平台。前缘部分由不同于形成后缘部分的第二材料的第一材料形成。第一材料具有比第二材料高至少100°F的工作温度能力。还公开了一种燃气涡轮发动机。

5. 发明申请

WO2014137692A1 GAS TURBINE ENGINE LUBRICATION SYSTEM 审中-公开
标题翻译：气体涡轮发动机润滑系统
公开(公告)号：WO2014137692A1
公开(公告)日：2014-09-12
申请号：PCT/US2014/018577
申请日：2014-02-26
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： ROBERGE, Gary D.
IPC分类号： F02C7/06 , F01D25/18
CPC分类号： F02C7/06 , F01D25/18 , F02C3/107 , F02C7/36 , F02K3/06 , F05D2260/40311 , F05D2260/98
摘要： A gas turbine engine according to an exemplary aspect of the present disclosure includes, a shaft including at least one bearing, a speed change device in communication with the shaft, a first lubrication system in communication with the at least one bearing and a second lubrication system in communication with the speed change device.
摘要翻译：根据本公开的示例性方面的燃气涡轮发动机包括：轴，包括至少一个轴承，与轴连通的变速装置，与所述至少一个轴承连通的第一润滑系统和第二润滑系统与变速装置通信。

6. 发明申请

WO2014130494A1 GAS TURBINE ENGINE CORE UTILIZED IN BOTH COMMERCIAL AND MILITARY ENGINES 审中-公开
标题翻译：在两个商业和军事发动机中使用的气体涡轮发动机核心
公开(公告)号：WO2014130494A1
公开(公告)日：2014-08-28
申请号：PCT/US2014/017015
申请日：2014-02-19
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： ROBERGE, Gary D. , CARLTON, Richard A. , HUDSON, Eric A.
IPC分类号： F02K3/072 , F02K3/04 , F02C7/00
CPC分类号： F02C3/073 , F02C3/107 , F02C3/14 , F02C7/24 , F02K3/025 , F02K3/06 , F05D2220/32 , F05D2230/52 , F05D2230/60 , Y10T29/49236
摘要： A method of manufacturing a military engine includes the steps of designing a commercial engine core, including a combustor, a high pressure compressor driven by a high pressure turbine, and a low pressure turbine designed to drive a low pressure compressor, and a fan through a gear reduction. A high speed fan is attached to the low pressure turbine, such that the combustor, high pressure compressor, low and high pressure turbines from an engine designed for commercial purposes is utilized for military purposes. A gas turbine engine is also disclosed.
摘要翻译：一种制造军用发动机的方法包括以下步骤：设计包括燃烧器，由高压汽轮机驱动的高压压缩机和设计成驱动低压压缩机的低压涡轮机的商业发动机芯，以及风扇通过齿轮减速。将高速风扇连接到低压涡轮机，使得用于商业目的的发动机的燃烧器，高压压缩机，低压和高压涡轮机用于军事目的。还公开了一种燃气涡轮发动机。

7. 发明申请

WO2006110124A2 EJECTOR COOLING OF OUTER CASE FOR TIP TURBINE ENGINE 审中-公开
标题翻译：推进涡轮发动机外壳的外壳冷却
公开(公告)号：WO2006110124A2
公开(公告)日：2006-10-19
申请号：PCT/US2004/040097
申请日：2004-12-01
申请人： UNITED TECHNOLOGIES CORPORATION , SUCIU, Gabriel L. , ROBERGE, Gary D.
发明人： SUCIU, Gabriel L. , ROBERGE, Gary D.
IPC分类号： F02C3/073 , F02K3/068 , F01D25/14
CPC分类号： F02C3/045 , F01D5/022 , F01D25/12 , F01D25/14 , F02C3/073 , F02C7/18 , F02K3/068 , Y02T50/675
摘要： A tip turbine engine includes a combustor radially outward of a fan. In order to reduce the heat transfer from the combustor and the high-energy gas stream generated by the combustor, a cold air ejector radially outward of the combustor extends from a forward end of the nacelle to a point rearward of the combustor and an exhaust mixer. The cold air ejector includes an annular inlet at the forward end of the nacelle. The cold air ejector draws air over the outer engine cases to provide a boundary between the nacelle and the hot outer engine case. The layer of air being pulled past the engine cases ejects the heat, thereby preventing the heat from escaping into the nacelle or engine bay.
摘要翻译：尖端涡轮发动机包括风扇径向向外的燃烧器。为了减少来自燃烧器的热传递和由燃烧器产生的高能量气体流，燃烧器径向向外的冷空气喷射器从机舱的前端延伸到燃烧器后方的一个点，并且排气混合器。冷空气喷射器包括在机舱前端的环形入口。冷空气喷射器将空气吸引在外部发动机壳体上，以提供机舱和热外部发动机壳体之间的边界。被拉动通过发动机箱的空气层排出热量，从而防止热量逸出到机舱或发动机舱中。

8. 发明申请

WO2006059982A1 REMOTE ENGINE FUEL CONTROL AND ELECTRONIC ENGINE CONTROL FOR TURBINE ENGINE 审中-公开
标题翻译：用于涡轮发动机的远程发动机燃油控制和电子发动机控制
公开(公告)号：WO2006059982A1
公开(公告)日：2006-06-08
申请号：PCT/US2004/040000
申请日：2004-12-01
申请人： UNITED TECHNOLOGIES CORPORATION , SUCIU, Gabriel L. , ROBERGE, Gary D. , MERRY, Brian
发明人： SUCIU, Gabriel L. , ROBERGE, Gary D. , MERRY, Brian
IPC分类号： F02C3/073 , F02C9/26 , F02K3/068
CPC分类号： F02C9/26 , F01D5/022 , F02C3/073 , F02C7/32 , F02C9/42 , F02K3/068
摘要： A controller is mounted remotely from a turbine engine and provided with an independent power source (120, 138). The controller may be an engine controller (112) generating control signals based upon user inputs and sensor inputs, or a fuel controller (114) controlling a supply of fuel to the turbine engine (10), or both. Each controller includes a power source independent of the turbine engine, i.e. the power source supplies power even when the turbine and fan of the turbine engine (10) are not turning. A single wire harness and a single fuel line (118) connect the engine controller (112) and the fuel controller (114) to the turbine engine (10).
摘要翻译：控制器从涡轮发动机远程安装并且设置有独立的电源（120,138）。控制器可以是基于用户输入和传感器输入产生控制信号的发动机控制器（112），或者控制向涡轮发动机（10）供应燃料的燃料控制器（114），或两者。每个控制器包括独立于涡轮发动机的电源，即即使当涡轮发动机（10）的涡轮机和风扇不转动时，电源也能够供电。单个线束和单个燃料管线（118）将发动机控制器（112）和燃料控制器（114）连接到涡轮发动机（10）。

9. 发明申请

WO2015054244A1 BONDED COMBUSTOR WALL FOR A TURBINE ENGINE 审中-公开
标题翻译：用于涡轮发动机的粘合式搅拌机壁
公开(公告)号：WO2015054244A1
公开(公告)日：2015-04-16
申请号：PCT/US2014/059486
申请日：2014-10-07
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： ROBERGE, Gary D.
IPC分类号： F02C3/14 , F02C7/20 , F23R3/42 , F23M5/04
CPC分类号： F23R3/002 , F02C7/18 , F23R3/005 , F23R3/007 , F23R3/06 , F23R2900/00017 , F23R2900/00018 , F23R2900/03042 , F23R2900/03044
摘要： A combustor wall is provided for a turbine engine. The combustor wall includes a shell, a heat shield and a combustion chamber. The heat shield is connected to the shell by a bonded connection, and defines a portion of the combustion chamber. A cooling cavity is defined between the shell and the heat shield.
摘要翻译：为涡轮发动机提供燃烧器壁。燃烧器壁包括壳体，隔热罩和燃烧室。隔热罩通过粘合连接连接到壳体，并且限定燃烧室的一部分。在外壳和隔热罩之间限定一个冷却腔。

10. 发明申请

WO2014164426A1 TURBINE ENGINE ADAPTIVE LOW LEAKAGE AIR SEAL 审中-公开
标题翻译：涡轮发动机适应性低泄漏空气密封
公开(公告)号：WO2014164426A1
公开(公告)日：2014-10-09
申请号：PCT/US2014/022403
申请日：2014-03-10
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： ROBERGE, Gary D.
IPC分类号： F01D11/08 , F02C7/28
CPC分类号： F01D11/20 , F05D2300/507 , F16J15/43
摘要： An air seal includes a sealing gland configured to retain a ferro-fluid and one or more seals. A portion of the one or more seals is configured to extend into the sealing gland. A gas turbine engine, includes the air seal. A method of sealing low pressure air from high pressure air, includes the steps of providing a sealing gland configured to retain a ferro-fluid, distributing the ferro-fluid into the sealing gland, providing one or more seals, wherein a portion of the one or more seals is configured to extend into the sealing gland, and removing the ferro-fluid from the sealing gland.
摘要翻译：空气密封件包括被配置为保持铁流体和一个或多个密封件的密封压盖。一个或多个密封件的一部分被构造成延伸到密封压盖中。燃气涡轮发动机包括空气密封。一种从高压空气密封低压空气的方法包括以下步骤：提供密封压盖，其被配置成保持铁流体，将铁水流体分配到密封压盖中，提供一个或多个密封件，其中一个或更多的密封件构造成延伸到密封压盖中，并且从密封压盖去除铁液。

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