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    Variable vane assemblies configured for non-axisymmetric actuation
    12.
    发明授权
    Variable vane assemblies configured for non-axisymmetric actuation 有权

    公开(公告)号：US10815802B2

    公开(公告)日：2020-10-27

    申请号：US16222548

    申请日：2018-12-17

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Dilip Prasad

    IPC: F01D9/04 ,  F01D25/04

    Abstract: A variable vane assembly may comprise a first vane and a second vane. The first vane may comprise a first strut portion and a first flap portion. The first flap portion may be configured to pivot relative to the first strut portion. The second vane may comprise a second strut portion and a second flap portion. The second flap portion may be configured to pivot relative to the second strut portion. The first flap may be configured to pivot independently of the second flap.

    Flutter damper for a turbofan engine
    14.
    发明授权
    Flutter damper for a turbofan engine 有权

    公开(公告)号：US10578016B2

    公开(公告)日：2020-03-03

    申请号：US15452619

    申请日：2017-03-07

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Derek J. Michaels ,  Dilip Prasad

    IPC: F01D25/04 ,  F02C7/045 ,  F02C7/057 ,  F01D25/06 ,  F01D5/26 ,  F02C9/00 ,  B64D33/02

    Abstract: Disclosed is a flutter damper, including an acoustic liner configured for peak acoustical energy absorption at a frequency range that is greater than a frequency range associated with fan flutter, a chamber, and a piezoelectric element disposed within a first surface of the chamber, and the chamber being configured for peak acoustical energy absorption at a frequency range that is associated with one or more fan flutter modes, and wherein the piezoelectric element is operatively connected to an electronic engine control.

    Acoustic Treatment to Mitigate Fan Noise
    18.
    发明申请
    Acoustic Treatment to Mitigate Fan Noise 审中-公开
    声音处理以减轻风扇噪音

    公开(公告)号：US20150337684A1

    公开(公告)日：2015-11-26

    申请号：US14760719

    申请日：2014-02-19

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： David A. Topol ,  Bruce L. Morin ,  Dilip Prasad ,  Thomas J. Ouellette

    IPC: F01D25/24 ,  F01D1/02 ,  F01D5/02

    CPC classification number: F01D25/24 ,  F01D1/02 ,  F01D5/021 ,  F02C7/045 ,  F05D2220/32 ,  F05D2250/283 ,  F05D2260/96

    Abstract: A gas turbine engine has a propulsor including a fan and a liner positioned upstream of the fan. The liner has a backing plate, a cellular structure with cells extending from the backing plate, and a perforated sheet with a depth defined as a distance between the perforated sheet and the backing sheet. The depth is selected to achieve a desired ratio of the depth relative to a gap?. A depth to gap ratio is substantially in a range of 0.035 to 0.08. A method is also disclosed.

    Abstract translation: 燃气涡轮发动机具有包括风扇和位于风扇上游的衬垫的推进器。 衬垫具有背板，具有从背板延伸的单元的多孔结构以及被定义为多孔板和背衬板之间距离的深度的多孔板。 选择深度以实现相对于间隙α的深度的期望比率。 深度与间隙比基本上在0.035至0.08的范围内。 还公开了一种方法。

    Gas turbine engine fan blade airfoil profile
    19.
    发明授权
    Gas turbine engine fan blade airfoil profile 有权
    燃气涡轮发动机风扇叶片翼型

    公开(公告)号：US08997494B2

    公开(公告)日：2015-04-07

    申请号：US13664647

    申请日：2012-10-31

    Applicant: United Technologies Corporation

    Inventor： Sue-Li Chuang ,  Yuan Dong ,  Sanjay S. Hingorani ,  Dilip Prasad

    IPC: F02C1/00 ,  F02G3/00 ,  F04D29/38 ,  F01D5/14

    CPC classification number: F04D29/384 ,  F01D5/141 ,  F05D2220/36 ,  F05D2250/74 ,  Y02T50/672 ,  Y02T50/673 ,  Y10T137/0536 ,  Y10T137/0645

    Abstract: A fan blade for a gas turbine engine includes an airfoil that includes leading and trailing edges joined by pressure and suction sides to provide an exterior airfoil surface that extends in a radial direction to a tip. The external airfoil surface is formed in substantial conformance with multiple cross-sectional profiles of the airfoil described by a set of Cartesian coordinates set forth in Table 1. The Cartesian coordinates are provided by an axial coordinate scaled by a local axial chord. A circumferential coordinate is scaled by the local axial chord, and a span location. The local axial chord corresponds to a width of the airfoil between the leading and trailing edges at the span location.

    Abstract translation: 用于燃气涡轮发动机的风扇叶片包括翼型件，其包括通过压力和吸力侧连接的前缘和后缘，以提供沿径向方向延伸到尖端的外部翼面。 外部翼面表面基本上符合由表1中所示的一组笛卡尔坐标所描述的翼型的多个横截面轮廓。笛卡尔坐标由通过局部轴向弦缩放的轴向坐标提供。 圆周坐标由局部轴向弦和跨度位置缩放。 局部轴向弦对应于跨距处的前缘和后缘之间的翼型的宽度。

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