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公开(公告)号：EP3055530A4
公开(公告)日：2016-11-09
申请号：EP14852801
申请日：2014-10-07
Applicant: UNITED TECHNOLOGIES CORP
Inventor： ROBERGE GARY D , COOK III GRANT O
CPC classification number: F23R3/002 , F02C7/18 , F23R3/005 , F23R3/007 , F23R3/06 , F23R2900/00017 , F23R2900/00018 , F23R2900/03042 , F23R2900/03044
Abstract: 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.
Abstract translation: 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。
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公开(公告)号：EP2964927A4
公开(公告)日：2016-11-09
申请号：EP14759478
申请日：2014-02-26
Applicant: UNITED TECHNOLOGIES CORP
Inventor： ROBERGE GARY D
CPC classification number: F02C7/06 , F01D25/18 , F02C3/107 , F02C7/36 , F02K3/06 , F05D2260/40311 , F05D2260/98
Abstract: 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.
Abstract translation: 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。
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Patent Agency Ranking
公开(公告)号：EP2954167A4
公开(公告)日：2016-06-08
申请号：EP14749072
申请日：2014-02-04
Applicant: UNITED TECHNOLOGIES CORP
Inventor： ROBERGE GARY D
CPC classification number: 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
Abstract: 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.
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24.发明公开
公开(公告)号：EP2971670A4
公开(公告)日：2016-12-14
申请号：EP13875661
申请日：2013-11-06
Applicant: UNITED TECHNOLOGIES CORP
Inventor： ROBERGE GARY D
CPC classification number: F02K3/115 , F01D9/065 , F02C7/06 , F02C7/14 , F02C7/18 , F02K3/06 , F02K3/105 , F05D2210/12 , F05D2240/123 , F05D2240/124 , F05D2250/182 , F05D2250/60 , F05D2260/20 , F05D2260/213 , F05D2260/4031 , F05D2260/98 , Y02T50/676
Abstract: An oil cooling system and method are provided for use with respect to a lubricated mechanical system within a bypass configured gas turbine engine. A surface cooler is fluidly linked to the lubricated mechanical system to receive oil from the lubricated mechanical system for cooling and reuse. In an embodiment, the surface cooler is mounted on an existing surface within the bypass airflow path of the bypass configured gas turbine engine to provide effective cooling while avoiding the introduction of additional aerodynamic disturbances in the bypass path. In an embodiment, the surface cooler is mounted on the fan casing or on a fan exit guide vane.
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公开(公告)号：EP2956649A4
公开(公告)日：2016-10-12
申请号：EP14751728
申请日：2014-01-24
Applicant: UNITED TECHNOLOGIES CORP
Inventor： ROBERGE GARY D
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26.发明公开
公开(公告)号：EP2959149A4
公开(公告)日：2016-03-23
申请号：EP14754278
申请日：2014-02-19
Applicant: UNITED TECHNOLOGIES CORP
Inventor： ROBERGE GARY D , CARLTON RICHARD A , HUDSON ERIC A
CPC classification number: F02C3/073 , F02C3/107 , F02C3/14 , F02C7/24 , F02K3/025 , F02K3/06 , F05D2220/32 , F05D2230/52 , F05D2230/60 , Y10T29/49236
Abstract: 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.
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27.发明公开TURBOFAN ENGINE INCLUDING THIRD FLOWPATH EXHAUST NOZZLE 有权MANTELSTROM-TRIEBWERK MIT DRITTERSTRÖMUNGSWEGAUSSTROMDÜSE
公开(公告)号：EP2959146A4
公开(公告)日：2016-03-23
申请号：EP14754377
申请日：2014-02-14
Applicant: UNITED TECHNOLOGIES CORP
Inventor： ROBERGE GARY D
CPC classification number: F02K1/1207 , F02K1/008 , F02K1/1292 , F02K1/38 , F02K3/02 , F02K3/075 , F02K3/077 , F05D2240/128 , F05D2250/36
Abstract: 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.
Abstract translation: 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。 在第二流路的径向外侧的第三流路在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独立且有选择地可调节的。 用于操作涡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运转。
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