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    VARIABLE VANE SCHEDULING BASED ON FLIGHT CONDITIONS FOR INCLEMENT WEATHER
    1.
    发明申请
    VARIABLE VANE SCHEDULING BASED ON FLIGHT CONDITIONS FOR INCLEMENT WEATHER 审中-公开
    基于飞行天气条件的变幅调度

    公开(公告)号：WO2013116125A2

    公开(公告)日：2013-08-08

    申请号：PCT/US2013023357

    申请日：2013-01-28

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： ROSE BECKY E ,  BRILLIANT LISA I

    IPC: F02C9/20

    CPC classification number: B64D45/00 ,  B64D2033/022 ,  F01D17/162 ,  F02C7/05 ,  F02C9/20 ,  F04D27/0292 ,  F04D29/563 ,  F05D2270/114

    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.

    Abstract translation: 根据本公开的示例性方面的保护燃气涡轮发动机的方法包括确定飞行器的至少一个飞行状况并将至少一个飞行状况与编程状态进行比较的步骤。 该方法还包括以下步骤：如果将至少一个飞行条件与编程的飞行条件进行比较的步骤确定已满足编程的飞行条件，则将低压压缩机的多个入口叶片从第一位置移动到第二位置， 用多个入口叶片偏转任何异物。

    LOW PRESSURE RATIO FAN ENGINE HAVING A DIMENSIONAL RELATIONSHIP BETWEEN INLET AND FAN SIZE
    5.
    发明公开
    LOW PRESSURE RATIO FAN ENGINE HAVING A DIMENSIONAL RELATIONSHIP BETWEEN INLET AND FAN SIZE 审中-公开
    与小的压力比的风扇马达和之间的入口和风扇尺寸的尺寸关系

    公开(公告)号：EP3052789A4

    公开(公告)日：2016-11-09

    申请号：EP14850031

    申请日：2014-09-18

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： LORD WESLEY K ,  MALECKI ROBERT E ,  QIU YUAN ,  ROSE BECKY E ,  GILSON JONATHAN

    IPC: F02C7/36 ,  F02C7/04 ,  F02K3/068

    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 section including a fan, the fan including a plurality of fan blades, a diameter of the fan having a dimension D that is based on a dimension of the fan blades, each fan blade having a leading edge, and a forward most portion on the leading edges of the fan blades in a first reference plane, a turbine section including a high pressure turbine and a low pressure turbine, the low pressure turbine driving the fan, a nacelle including an inlet portion forward of the fan, a forward edge on the inlet portion in a second reference plane, and a length of the inlet portion having a dimension L measured along an engine axis between the first reference plane and the second reference plane. A dimensional relationship of L/D is no more than 0.45.

    Abstract translation: 。根据实施例的示例，一种燃气涡轮发动机组件包括，除其他事项外，风扇确实具有风扇叶片的复数。 风扇的直径具有尺寸D做是基于所述风扇叶片的尺寸。 每个风扇叶片具有领先优势。 的入口部分向前风扇位于。 入口部分的长度具有至少一些风扇叶片的和在入口部分的前边缘的前缘的位置之间的尺寸L。 L的尺寸关系/ D是约0.2至约12:45之间。

    HIGH TURNING FAN EXIT STATOR
    7.
    发明公开
    HIGH TURNING FAN EXIT STATOR 审中-公开
    高转速风扇提取器

    公开(公告)号：EP2809929A4

    公开(公告)日：2015-04-15

    申请号：EP13778582

    申请日：2013-01-28

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： BRILLIANT LISA I ,  ROSE BECKY E ,  DONG YUAN ,  BALAMUCKI STANLEY J

    IPC: F02K3/072 ,  F02C7/36

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

    Abstract: A turbine engine includes 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.

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