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    A GAS TURBINE ENGINE AND NACELLE NOISE ATTENUATION STRUCTURE
    1.
    发明申请
    A GAS TURBINE ENGINE AND NACELLE NOISE ATTENUATION STRUCTURE 审中-公开
    燃气涡轮发动机与纳机噪声衰减结构

    公开(公告)号：WO2014028078A3

    公开(公告)日：2014-04-10

    申请号：PCT/US2013037686

    申请日：2013-04-23

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： GILSON JONATHAN ,  MAY MOLLY M ,  WELCH DAVID A ,  SAWYERS-ABBOTT NIGEL DAVID

    IPC: F02C7/045 ,  F02K1/34

    CPC classification number: F02C3/04 ,  F02C3/107 ,  F02C7/045 ,  F02K3/06 ,  F04D29/545 ,  F04D29/644 ,  F04D29/664

    Abstract: A nacelle structure for a gas turbine engine assembly includes a fan case, and inlet, and a noise attenuation device. The fan case is configured to be disposed about a fan section of the gas turbine engine, which fan section has a diameter D. The inlet is attached to the fan case and extends axially forward of the fan case. A hilite of the inlet is spaced a distance L from a region in which the fan section is configured to be disposed. A ratio L/D is less than about 0.6. The noise attenuation structure covers a portion of an inner surface of the fan case and the inlet.

    Abstract translation: 用于燃气涡轮发动机组件的机舱结构包括风扇壳体和入口以及噪声衰减装置。 风扇外壳被配置为围绕燃气涡轮发动机的风扇部分设置，该风扇部分具有直径D.入口连接到风扇外壳并且在风扇外壳的轴向前方延伸。 入口的hilite与配置有风扇部分的区域间隔距离L. 比值L / D小于约0.6。 噪声衰减结构覆盖风扇外壳的内表面和入口的一部分。

    ACOUSTIC LINER WITH VARIED PROPERTIES
    2.
    发明申请
    ACOUSTIC LINER WITH VARIED PROPERTIES 审中-公开
    具有不同特性的声学衬里

    公开(公告)号：WO2014197035A3

    公开(公告)日：2015-02-19

    申请号：PCT/US2014023024

    申请日：2014-03-11

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： GILSON JONATHAN ,  BALTAS CONSTANTINE

    IPC: F02C7/045 ,  F01D25/24 ,  F02C7/24

    CPC classification number: F02C7/045 ,  F01D25/24 ,  F02C3/107 ,  F02C7/24 ,  F02K1/827 ,  F05D2240/40 ,  F05D2250/00 ,  F05D2250/283 ,  F05D2250/37 ,  F05D2260/963

    Abstract: A geared turbofan engine includes a first rotor, a fan, a second rotor, a gear train, a fan casing, a nacelle and a plurality of discrete acoustic liner segments. The fan is connected to the first rotor and is capable of rotation at frequencies between 200 and 6000 Hz and has a fan pressure ratio of between 1.25 and 1.60. The gear train connects the first rotor to the second rotor. The fan casing and nacelle are arranged circumferentially about a centerline and define a bypass flow duct in which the fan is disposed. The plurality of discrete acoustic liner segments with varied geometric properties are disposed along the bypass flow duct.

    Abstract translation: 齿轮涡扇发动机包括第一转子，风扇，第二转子，齿轮系，风扇壳体，机舱和多个离散的声学衬垫段。 风扇连接到第一转子并且能够在200和6000Hz之间的频率旋转，并且风扇压力比在1.25和1.60之间。 齿轮系将第一转子连接到第二转子。 风扇壳体和机舱围绕中心线周向布置并且限定其中设置风扇的旁通流动管道。 具有不同几何特性的多个离散声学衬垫段沿着旁路流动管道设置。

    GEARED TURBOFAN ENGINE HAVING A REDUCED NUMBER OF FAN BLADES AND IMPROVED ACOUSTICS
    6.
    发明公开
    GEARED TURBOFAN ENGINE HAVING A REDUCED NUMBER OF FAN BLADES AND IMPROVED ACOUSTICS 审中-公开
    TURBOGEBLÄSEMOTORMIT REDUZIERTER ANZAHL VONGEBLÄSESCHAUFELNUND VERBESSERTER AKUSTIK

    公开(公告)号：EP2971535A4

    公开(公告)日：2017-02-15

    申请号：EP14770545

    申请日：2014-02-21

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： BALTAS CONSTANTINE ,  GILSON JONATHAN

    IPC: F01D5/14 ,  F01D5/00 ,  F02C7/00

    CPC classification number: F01D5/141 ,  F05D2220/36 ,  Y02T50/671 ,  Y02T50/673

    Abstract: A rotor blade comprises an airfoil extending radially from a root section to a tip section and axially from a leading edge to a trailing edge, the leading and trailing edges defining a curvature therebetween. The curvature determines a relative exit angle at a relative span height between the root section and the tip section, based on an incident flow velocity at the leading edge of the airfoil and a rotational velocity at the relative span height. In operation of the rotor blade, the relative exit angle determines a substantially flat exit pressure ratio profile for relative span heights from 75% to 95%, wherein the exit pressure ratio profile is constant within a tolerance of 10% of a maximum value of the exit pressure ratio profile.

    Abstract translation: 转子叶片包括从根部到顶端部分径向延伸并且从前缘到后缘的轴向延伸的翼型件，前缘和后缘在它们之间限定曲率。 基于在翼型的前缘处的入射流速和相对跨度高度处的旋转速度，曲率确定根部和尖端部分之间的相对跨度高度处的相对出射角。 在转子叶片的操作中，相对出口角度确定从75％至95％的相对跨度高度的基本上平坦的出口压力比分布，其中出口压力比分布在±10％ 出口压力比。

    LOW PRESSURE RATIO FAN ENGINE HAVING A DIMENSIONAL RELATIONSHIP BETWEEN INLET AND FAN SIZE
    7.
    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。

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