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    HIGH TURNING FAN EXIT STATOR
    2.
    发明申请
    HIGH TURNING FAN EXIT STATOR 审中-公开
    高转速风扇出口定子

    公开(公告)号：WO2013158181A1

    公开(公告)日：2013-10-24

    申请号：PCT/US2013/023383

    申请日：2013-01-28

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： BRILLIANT, Lisa I. ,  ROSE, Becky E. ,  DONG, Yuan ,  BALAMUCKI, Stanley J.

    IPC: F02G1/00

    CPC classification number: F01D5/141 ,  F02C7/36 ,  F02K3/072 ,  F05D2220/36 ,  Y02T50/673

    Abstract: A turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan section that rotates about a longitudinal axis and a compressor section. The turbine engine also includes a fan exit stator located between the fan section and the compressor section, the fan exit stator including an airfoil. The airfoil defines an entrance angle with respect to a leading edge of the airfoil and a line parallel to the longitudinal axis, and the airfoil defines an exit angle with respect to a trailing edge of the airfoil and a line parallel to the longitudinal axis. A difference between the entrance angle and the exit angle is between about 45° and about 65°. The turbine engine also includes a turbine section, and a portion of the compressor section is driven by a portion of the turbine section.

    Abstract translation: 根据本公开的示例性方面的涡轮发动机尤其包括围绕纵向轴线和压缩机部分旋转的风扇部分。 涡轮发动机还包括位于风扇部分和压缩机部分之间的风扇出口定子，风扇出口定子包括翼型件。 翼型件相对于翼型件的前缘和平行于纵向轴线的线限定入口角，并且翼型件相对于翼型件的后缘和平行于纵向轴线的线限定出口角。 入射角和出射角之间的差异在大约45°和大约65°之间。 涡轮发动机还包括涡轮部分，并且压缩机部分的一部分由涡轮部分的一部分驱动。

    LOW PRESSURE RATIO FAN ENGINE HAVING A DIMENSIONAL RELATIONSHIP BETWEEN INLET AND FAN SIZE
    3.
    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。

    LPC FLOWPATH SHAPE WITH GAS TURBINE ENGINE SHAFT BEARING CONFIGURATION
    4.
    发明申请
    LPC FLOWPATH SHAPE WITH GAS TURBINE ENGINE SHAFT BEARING CONFIGURATION 审中-公开
    LPC涡轮形状与气体涡轮发动机轴承轴承配置

    公开(公告)号：WO2015017042A1

    公开(公告)日：2015-02-05

    申请号：PCT/US2014/043184

    申请日：2014-06-19

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： MERRY, Brian D. ,  SUCIU, Gabriel L. ,  BRILLIANT, Lisa I. ,  ROSE, Becky E. ,  DONG, Yuan ,  BALAMUCKI, Stanley J.

    IPC: F02C3/13

    CPC classification number: F02C9/18 ,  F01D5/143 ,  F02K3/075 ,  F04D19/028 ,  F04D29/547 ,  F05D2250/314 ,  F05D2260/98 ,  Y02T50/673

    Abstract: A gas turbine engine includes a core housing that includes an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flowpath. A shaft provides a rotational axis. A hub is operatively supported by the shaft. A rotor is connected to the hub and supports a compressor section. The compressor section is arranged in a core flow path axially between the inlet case flow path and the intermediate case flow path. The core flowpath has an inner diameter and an outer diameter. At least a portion of inner diameter has an increasing slope angle relative to the rotational axis. A bearing is mounted to the hub and supports the shaft relative to one of the intermediate case and the inlet case.

    Abstract translation: 燃气涡轮发动机包括芯壳体，其包括分别设置入口壳体流动路径和中间壳体流路的入口壳体和中间壳体。 轴提供旋转轴。 轮毂由轴可操作地支撑。 转子连接到轮毂并支撑压缩机部分。 压缩机部分布置在轴向上在入口壳体流动路径和中间壳体流动路径之间的芯流动路径中。 核心流路具有内径和外径。 内径的至少一部分相对于旋转轴具有增加的倾斜角。 轴承安装到轮毂上并相对于中间壳体和入口壳体之一支撑轴。

    VARIABLE VANE SCHEDULING BASED ON FLIGHT CONDITIONS FOR INCLEMENT WEATHER
    6.
    发明申请
    VARIABLE VANE SCHEDULING BASED ON FLIGHT CONDITIONS FOR INCLEMENT WEATHER 审中-公开

    公开(公告)号：WO2013116125A3

    公开(公告)日：2013-08-08

    申请号：PCT/US2013/023357

    申请日：2013-01-28

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： ROSE, Becky E. ,  BRILLIANT, Lisa I

    IPC: F02C7/05

    Abstract: A method of protecting a gas turbine engine according an exemplary aspect of the present disclosure includes, among other things, the steps of determining at least one flight condition of an aircraft and comparing the at least one flight condition to a programmed condition. The method further includes the steps of moving a plurality of inlet vanes of a low pressure compressor from a first position to a second position if the step of comparing the at least one flight condition to the programmed flight condition determines the programmed flight condition are met and deflecting any foreign objects with the plurality of inlet vanes.

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