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    MOUNTING SYSTEMS FOR GAS TURBINE ENGINES
    51.
    发明公开
    MOUNTING SYSTEMS FOR GAS TURBINE ENGINES 审中-公开
    MONTAGESYSTEMEFÜRGASTURBINENMOTOREN

    公开(公告)号：EP3049657A1

    公开(公告)日：2016-08-03

    申请号：EP14849046.9

    申请日：2014-08-01

    Applicant: United Technologies Corporation

    Inventor： HILL, James D. ,  SUCIU, Gabriel L. ,  CHANDLER, Jesse M.

    IPC: F02C7/20 ,  B64D27/10

    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。 压缩机壳体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。 安装结构的轴向后部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且连接前后安装结构，从而跨过入口和出口框架桥接发动机负载，以减少压缩机壳体部分的负载引起的变形。

    CERAMIC LINER FOR A TURBINE EXHAUST CASE
    52.
    发明公开
    CERAMIC LINER FOR A TURBINE EXHAUST CASE 审中-公开
    KERAMISCHE AUSKLEIDUNGFÜREINETURBINENABGASGEHÄUSE

    公开(公告)号：EP3044442A2

    公开(公告)日：2016-07-20

    申请号：EP14860946.4

    申请日：2014-08-19

    Applicant: United Technologies Corporation

    Inventor： SUCIU, Gabriel L. ,  CHANDLER, Jesse M.

    IPC: F02C7/20 ,  F02C7/24 ,  F02K1/04 ,  F01D9/04 ,  F01D25/24

    Abstract: A gas turbine engine includes a core engine including a central engine axis and a nacelle surrounding the core engine. At least a portion of the nacelle is axially movable relative to the core engine between open and fully closed positions. A ceramic-based liner is located at an aft portion of the core engine. The ceramic-based component mechanically interfaces with the movable portion of the nacelle when the nacelle is in the fully closed position. A turbine section and a method of accommodating thermally-induced dimensional change of engine components are also disclosed.

    Abstract translation: 燃气涡轮发动机包括具有中心发动机轴线和围绕核心发动机的机舱的核心发动机。 机舱的至少一部分在开放位置和完全关闭位置之间相对于核心发动机可轴向移动。 陶瓷基衬套位于核心发动机的后部。 当机舱处于完全关闭位置时，陶瓷基部件与机舱的可移动部分机械地接合。 还公开了涡轮部分和容纳发动机部件的热致尺寸变化的方法。

    TWIN TARGET THRUST REVERSER MODULE
    53.
    发明公开
    TWIN TARGET THRUST REVERSER MODULE 审中-公开
    双目标推倒转模块

    公开(公告)号：EP2971728A2

    公开(公告)日：2016-01-20

    申请号：EP14807682.1

    申请日：2014-03-13

    Applicant: United Technologies Corporation

    Inventor： SUCIU, Gabriel L. ,  CHANDLER, Jesse M.

    IPC: F02K1/60 ,  F02K1/11

    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: 用于双燃气涡轮发动机推进系统的喷嘴组件包括可安装在第一燃气涡轮发动机的第一旁路通道和第二燃气涡轮发动机的第二旁路通道附近的壳体，第一和第二上门以及第一和第二下部门 门。 第一上部门和第二上部门以及第一下部门和第二下部门中的每一个枢转地安装到壳体，用于在收起位置和展开位置之间运动，其中通过第一和第二旁路通道的气流相对于 第一和第二燃气涡轮发动机。

    TWO SPOOL GAS GENERATOR WITH IMPROVED AIR PORTING
    54.
    发明公开
    TWO SPOOL GAS GENERATOR WITH IMPROVED AIR PORTING 审中-公开
    具有改进的空气两个螺旋气体发生器MOVE

    公开(公告)号：EP2943667A1

    公开(公告)日：2015-11-18

    申请号：EP13870920.9

    申请日：2013-05-10

    Applicant: United Technologies Corporation

    Inventor： SUCIU, Gabriel L. ,  CHANDLER, Jesse M. ,  LORD, Wesley K.

    IPC: F02C3/04 ,  F02C9/16

    CPC classification number: F02C7/185 ,  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.

    OFFSET CORE ENGINE ARCHITECTURE
    55.
    发明公开
    OFFSET CORE ENGINE ARCHITECTURE 审中-公开
    VERSETZTE KERNTRIEBWERKSARCHITEKTUR

    公开(公告)号：EP2915988A1

    公开(公告)日：2015-09-09

    申请号：EP15157466.2

    申请日：2015-03-03

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： SUCIU, Gabriel L. ,  HILL, James D. ,  CHANDLER, Jesse M.

    IPC: F02K3/12 ,  F02C3/10 ,  F02C7/05

    CPC classification number: F02C3/14 ,  F02C3/06 ,  F02C3/10 ,  F02C6/02 ,  F02C7/05 ,  F02K3/12 ,  F05D2220/32 ,  F05D2250/314

    Abstract: A gas turbine engine (20) has a propulsion unit and a gas generating core (28). The propulsion unit includes a fan (24) and a free turbine (42) that is connected to drive the fan (24) about a first axis (X). The gas generating core (28) includes a compressor (30), a combustion section (36) and a gas generating core turbine (34). The compressor (30) and the gas generating core turbine (34) are configured to rotate about a second axis (Y). An inlet duct (46) is configured to deliver air from the fan (24) to the gas generating core (28). The inlet duct (46) has a crescent shaped cross-section near the fan (24).

    Abstract translation: 燃气涡轮发动机（20）具有推进单元和气体发生芯（28）。 推进单元包括风扇（24）和空气涡轮机（42），其被连接以围绕第一轴线（X）驱动风扇（24）。 气体发生芯（28）包括压缩机（30），燃烧部分（36）和气体发生芯涡轮机（34）。 压缩机（30）和气体发生芯涡轮机（34）构造成围绕第二轴线（Y）旋转。 入口管道（46）构造成将空气从风扇（24）输送到气体生成芯（28）。 入口管道（46）在风扇（24）附近具有新月形横截面。

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