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公开(公告)号：EP2943668A4
公开(公告)日：2016-01-20
申请号：EP13870696
申请日：2013-06-07
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SUCIU GABRIEL L , CHANDLER JESSE M
CPC classification number: F01D25/162 , F02C7/12 , F02C7/20 , F02C7/32 , F05D2220/325 , F05D2260/60 , Y02T50/675
Abstract: A gas turbine engine has a turbine section, and a housing enclosing the turbine section, with a mount structure secured to the housing for mounting and including internal flow passages for delivering air to remote locations.
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公开(公告)号：EP2929162A4
公开(公告)日：2016-01-06
申请号：EP13862563
申请日：2013-06-20
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SUCIU GABRIEL L , CHANDLER JESSE M
CPC classification number: F02C7/052 , B01D46/0023 , F02C7/12 , F05D2220/327 , F05D2260/40311 , F05D2260/607 , Y02T50/675
Abstract: A gas turbine engine has a first particle separator stage including a surface for impacting air at outer periphery of an air flow passage, capturing impacted particles at the outer periphery, and routing captured particles towards a second particle separator stage. Air inward of the first particle separator stage passes towards a core of the engine. Cleaner air upstream of the second particle separator stage is utilized for an air function at a location other than the core engine. A particle discharge is disposed downstream of said second particle separator stage.
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13.发明公开
公开(公告)号：EP2929163A4
公开(公告)日：2016-08-10
申请号：EP13862641
申请日：2013-06-20
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SUCIU GABRIEL L , CHANDLER JESSE M
CPC classification number: F02C7/18 , F01D25/12 , F02C9/18 , F05D2220/324 , F05D2220/327 , F05D2250/51 , Y02T50/675
Abstract: A gas turbine engine has a first source of air to be delivered into a core of the engine, and a second source of air, distinct from the first source of air and including separately controlled first and second fans, each delivering air into respective first and second conduits connected to distinct auxiliary applications.
Abstract translation: 燃气涡轮发动机具有要被输送到发动机的核心中的第一空气源和与第一空气源不同的第二气源，并且包括单独控制的第一和第二风扇，每个将空气输送到相应的第一和第 连接到不同辅助应用的第二导管。
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公开(公告)号：EP2932039A4
公开(公告)日：2015-12-23
申请号：EP13863829
申请日：2013-12-04
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SUCIU GABRIEL L , CHANDLER JESSE M , MERRY BRIAN D
CPC classification number: F01D5/225 , F01D5/34 , F01D21/045 , F04D29/023 , F04D29/321 , F05D2220/36 , F05D2230/53 , F05D2260/96 , F05D2300/121 , F05D2300/133 , F05D2300/173 , F05D2300/174 , F05D2300/603 , F05D2300/614 , Y02T50/672
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Patent Agency Ranking
公开(公告)号：EP2920068A4
公开(公告)日：2015-11-25
申请号：EP13856025
申请日：2013-10-17
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SUCIU GABRIEL L , CHANDLER JESSE M
CPC classification number: B64C5/02 , B64C1/26 , B64C5/06 , B64C9/02 , B64C19/00 , B64D27/14 , B64D33/04 , F02K1/56 , F02K1/78
Abstract: An aircraft includes a tail extending from a fuselage. The tail defines a structural box having first and second vertical stabilizers that support a horizontal stabilizer. The tail includes at least one sacrificial control surface and at least one primary control surface. The primary control surfaces maintain aircraft controllability in the event that the sacrificial control surface becomes inoperable.
Abstract translation: 飞机包括从机身延伸的尾部。 尾部限定了具有支撑水平稳定器的第一和第二垂直稳定器的结构箱。 尾部包括至少一个牺牲控制表面和至少一个主控制表面。 在牺牲控制表面变得不可操作的情况下，主控制面保持飞行器的可控性。
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公开(公告)号：EP3049657A4
公开(公告)日：2017-07-05
申请号：EP14849046
申请日：2014-08-01
Applicant: UNITED TECHNOLOGIES CORP
Inventor： HILL JAMES D , SUCIU GABRIEL L , CHANDLER JESSE M
CPC classification number: F04D29/644 , B64D27/26 , B64D2027/264 , B64D2027/266 , F01D25/243 , F02C7/20 , F04D29/324 , F04D29/522 , F05D2220/32 , Y02T50/44 , Y02T50/671
Abstract: A mounting system for a gas turbine engine includes a compressor case portion, an inlet frame, an outlet frame, and a mounting structure. The compressor case portion houses rotatable compressor blades. The inlet frame connects to an inlet end of the compressor case. The outlet frame connects to an outlet end of the compressor case portion at an end opposite the compressor case inlet end. An axially fore mounting structure of the mounting structure connects to the inlet frame. An axially aft mounting structure of the mounting structure connects to the outlet frame. A bridging structure of the mounting structure is offset from the compressor case and connects the fore and aft mounting structures, thereby bridging engine loads across the inlet and outlet frames to reduce load induced distortion of the compressor case portion.
Abstract translation: 用于燃气涡轮发动机的安装系统包括压缩机壳体部分，入口框架，出口框架和安装结构。 压缩机壳部分容纳可旋转的压缩机叶片。 入口框架连接到压缩机壳体的入口端。 出口框架在与压缩机壳体入口端相对的端部处连接到压缩机壳体部分的出口端。 安装结构的轴向前部安装结构连接到入口框架。 安装结构的轴向后安装结构连接到出口框架。 安装结构的桥接结构偏离压缩机壳体并连接前后安装结构，从而桥接入口框架和出口框架上的发动机负载以减少压缩机壳体部分的负载引起的变形。
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公开(公告)号：EP2971728A4
公开(公告)日：2016-11-23
申请号：EP14807682
申请日：2014-03-13
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SUCIU GABRIEL L , CHANDLER JESSE M
CPC classification number: F02K1/70 , F02K1/06 , F02K1/52 , F02K1/60 , F02K1/62 , F05D2220/323 , F05D2240/40
Abstract: A nozzle assembly for a dual gas turbine engine propulsion system includes a housing mountable proximate to a first bypass passage of a first gas turbine engine and a second bypass passage of a second gas turbine engine, first and second upper doors, and first and second lower doors. Each of the first and second upper doors and the first and second lower doors are pivotally mounted to the housing for movement between a stowed position and a deployed position in which airflow through the first and second bypass passages is redirected relative to respective centerline axes of the first and second gas turbine engines.
Abstract translation: 一种用于双燃气涡轮发动机推进系统的喷嘴组件，包括可靠近第一燃气涡轮发动机的第一旁路通道安装的壳体，以及第二燃气涡轮发动机的第二旁通通道，第一和第二上部门以及第一和第二下部 门。 第一和第二上部门以及第一和第二下部门中的每一个枢转地安装到壳体上，用于在收起位置和展开位置之间移动，在该位置中，穿过第一和第二旁路通道的气流相对于相应的中心线 第一和第二燃气涡轮发动机。
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公开(公告)号：EP2943670A4
公开(公告)日：2016-01-20
申请号：EP13870617
申请日：2013-06-04
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SUCIU GABRIEL L , CHANDLER JESSE M
CPC classification number: F02C7/36 , B64D27/10 , B64D2027/005 , F02C7/06 , F02C7/20 , F02C7/32 , F02K3/072 , F05D2240/90 , Y02T50/66
Abstract: A gas turbine engine has a first shaft including a first turbine rotor, and a second shaft including a second turbine rotor disposed downstream of the first turbine rotor. A third shaft includes a propulsor turbine positioned downstream of the second turbine rotor for driving a propeller. A mount ring is secured between the second turbine rotor and the propeller.
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19.发明公开TWO SPOOL GAS GENERATOR WITH IMPROVED AIR PORTING 审中-公开ZWEISPULENGASGENERATOR MIT VERBESSERTER LUFTPORTIERUNG
公开(公告)号：EP2943667A4
公开(公告)日：2016-01-20
申请号：EP13870920
申请日：2013-05-10
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SUCIU GABRIEL L , CHANDLER JESSE M , LORD WESLEY K
CPC classification number: F02C7/12 , F02C3/13 , F02C3/145 , F02C6/04 , F02C6/08 , F02C9/18 , F02K3/00 , F02K3/02 , F05D2220/3217 , F05D2220/3218
Abstract: In a featured embodiment, a gas turbine engine has a first compressor rotor driven by a first turbine rotor, and a second compressor rotor driven by a second turbine rotor. The second compressor rotor is upstream of the first compressor rotor and the first turbine rotor is upstream of the second turbine rotor. An air mixing system taps air from a location upstream of the first compressor rotor for delivery to an environmental control system. The air mixing system receives air from a first air source and a second air source. The first air source includes air at a first pressure upstream of the first compressor rotor. The second air source includes air at a lower second pressure. At least one valve controls a mixture of air from the first and second sources to achieve a predetermined pressure for the environmental control system.
Abstract translation: 在特征实施例中，燃气涡轮发动机具有由第一涡轮转子驱动的第一压缩机转子和由第二涡轮转子驱动的第二压缩机转子。 第二压缩机转子在第一压缩机转子的上游，第一涡轮转子位于第二涡轮转子的上游。 空气混合系统从第一压缩机转子的上游位置抽出空气，用于输送到环境控制系统。 空气混合系统从第一空气源和第二空气源接收空气。 第一空气源包括在第一压缩机转子的上游的第一压力下的空气。 第二空气源包括较低的第二压力的空气。 至少一个阀控制来自第一和第二源的空气的混合物以实现环境控制系统的预定压力。
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