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    GAS TURBINE ENGINE WITH SEPARATE CORE AND PROPULSION UNIT
    1.
    发明申请
    GAS TURBINE ENGINE WITH SEPARATE CORE AND PROPULSION UNIT 审中-公开
    具有独立核心和推进单元的气体涡轮发动机

    公开(公告)号：WO2013119527A1

    公开(公告)日：2013-08-15

    申请号：PCT/US2013/024704

    申请日：2013-02-05

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： SUCIU, Gabriel L. ,  LORD, Wesley K. ,  DYE, Christopher

    IPC: F02K3/06 ,  F02K3/02 ,  F02C7/00 ,  F02K5/00

    CPC classification number: F02C3/145 ,  F02C7/36 ,  F02K3/025 ,  F05D2250/314

    Abstract: A gas turbine engine includes a propulsion unit mounted to rotate about a first axis, and a core engine mounted to rotate about a second axis, and wherein the first and second axes are non-parallel. A gas turbine engine includes a propulsion unit driven by a free turbine which is adjacent to the propulsion unit and an associated fan, and having a gas generator core engine including a compressor, combustor and turbine section. A method is also disclosed.

    Abstract translation: 燃气涡轮发动机包括安装成围绕第一轴线旋转的推进单元和安装成围绕第二轴线旋转的核心发动机，并且其中第一和第二轴线是不平行的。 燃气涡轮发动机包括由与推进单元相邻的自由涡轮机驱动的推进单元和相关联的风扇，并且具有包括压缩机，燃烧器和涡轮机部分的气体发生器核心发动机。 还公开了一种方法。

    TWO SPOOL GAS GENERATOR WITH IMPROVED AIR PORTING
    2.
    发明申请
    TWO SPOOL GAS GENERATOR WITH IMPROVED AIR PORTING 审中-公开
    具有改进空气压力的两个气缸发电机

    公开(公告)号：WO2014109786A1

    公开(公告)日：2014-07-17

    申请号：PCT/US2013/040493

    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: F02C7/12 ,  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。

    LOW PRESSURE RATIO FAN ENGINE HAVING A DIMENSIONAL RELATIONSHIP BETWEEN INLET AND FAN SIZE
    5.
    发明申请
    LOW PRESSURE RATIO FAN ENGINE HAVING A DIMENSIONAL RELATIONSHIP BETWEEN INLET AND FAN SIZE 审中-公开
    低压风扇发动机在入口和风扇尺寸之间存在尺寸关系

    公开(公告)号：WO2015047842A1

    公开(公告)日：2015-04-02

    申请号：PCT/US2014/056203

    申请日：2014-09-18

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： LORD, Wesley K. ,  MALECKI, Robert E. ,  QIU, Yuan ,  ROSE, Becky E. ,  GILSON, Jonathan

    IPC: F02C7/36

    CPC classification number: F02K3/068 ,  F01D25/24 ,  F02C7/04 ,  F05D2220/36 ,  F05D2240/303 ,  F05D2260/40311 ,  F05D2260/96 ,  Y02T50/671

    Abstract: According to an example embodiment, a gas turbine engine assembly includes, among other things, a fan that has a plurality of fan blades. A diameter of the fan has a dimension D that is based on a dimension of the fan blades. Each fan blade has a leading edge. An inlet portion is situated forward of the fan. A length of the inlet portion has a dimension L between a location of the leading edge of at least some of the fan blades and a forward edge on the inlet portion. A dimensional relationship of L/D is between about 0.2 and about 0.45.

    Abstract translation: 根据示例性实施例，燃气涡轮发动机组件尤其包括具有多个风扇叶片的风扇。 风扇的直径具有基于风扇叶片的尺寸的尺寸D. 每个风扇叶片都有一个前沿。 入口部分位于风扇的前方。 入口部分的长度在至少一些风扇叶片的前缘的位置与入口部分的前边缘之间具有尺寸L。 L / D的尺寸关系为约0.2至约0.45。

    GAS TURBINE ENGINE INLET
    6.
    发明申请
    GAS TURBINE ENGINE INLET 审中-公开
    气体涡轮发动机入口

    公开(公告)号：WO2014137685A1

    公开(公告)日：2014-09-12

    申请号：PCT/US2014/018544

    申请日：2014-02-26

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： QIU, Yuan J. ,  MILLER, Robert M. ,  LORD, Wesley K. ,  HENDRICKS, Gavin

    IPC: F02C7/04 ,  F02C7/00

    CPC classification number: F02C7/04 ,  B64D2033/0286 ,  F01D5/02 ,  F01D17/105 ,  F01D25/24 ,  F02C3/04 ,  F02K3/06 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2240/303 ,  F05D2250/323 ,  F05D2250/511 ,  F05D2260/40 ,  Y02T50/671

    Abstract: A gas turbine engine that includes a fan nacelle and a core nacelle that provide a bypass flow path radially between. The fan nacelle has an inlet including a throat. The inlet has an inlet forward-most point. A fan is arranged in the bypass flow path and rotatable about an axis. The fan has a leading edge recessed from the inlet forward-most point an inlet length in an axial direction. A spinner has a spinner length from a spinner forward-most point to the leading edge. A ratio of the spinner length to inlet length is equal to or greater than about 0.5.

    Abstract translation: 一种燃气涡轮发动机，其包括在其之间径向提供旁通流动路径的风扇机舱和核心机舱。 风扇机舱具有包括喉部的入口。 入口具有入口最前面的点。 风扇布置在旁路流动路径中并可围绕轴线旋转。 风扇具有从入口最前端凹入的前缘，其轴向方向上的入口长度。 旋转器的旋转器长度从最远点到最前沿。 旋转器长度与入口长度的比例等于或大于约0.5。

    GAS TURBINE ENGINE WITH INLET PARTICLE SEPARATOR AND THERMAL MANAGEMENT
    8.
    发明申请
    GAS TURBINE ENGINE WITH INLET PARTICLE SEPARATOR AND THERMAL MANAGEMENT 审中-公开
    具有入口颗粒分离器和热管理的气体涡轮发动机

    公开(公告)号：WO2014078003A2

    公开(公告)日：2014-05-22

    申请号：PCT/US2013/065337

    申请日：2013-10-17

    Applicant: UNITED TECHNOLOGIES CORPORATION

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

    IPC: F02C7/052 ,  F02C7/12

    CPC classification number: F01D25/08 ,  F02C7/052 ,  Y02T50/675

    Abstract: A gas turbine engine includes a nose cone at an inlet end, and spaced radially inwardly of a nacelle. A compressor is downstream of the nose cone. A core inlet delivers air downstream of the nose cone into the compressor. An inlet particle separator includes a manifold for delivering air radially outwardly of the core inlet. Air delivered by the inlet particle separator passes over a heat exchanger before passing to an outlet.

    Abstract translation: 燃气涡轮发动机包括在入口端处的鼻锥体，并且在机舱的径向内侧间隔开。 压缩机在鼻锥的下游。 核心入口将鼻锥下游的空气输送到压缩机中。 入口颗粒分离器包括用于沿芯入口径向向外输送空气的歧管。 通过入口颗粒分离器输送的空气在通过出口之前通过热交换器。

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