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    GAS TURBINE ENGINE FAN BLADE AIRFOIL PROFILE
    1.
    发明申请
    GAS TURBINE ENGINE FAN BLADE AIRFOIL PROFILE 审中-公开
    燃气轮机发动机风叶风叶轮廓

    公开(公告)号：WO2014092833A3

    公开(公告)日：2014-08-14

    申请号：PCT/US2013061123

    申请日：2013-09-23

    Applicant: UNITED TECHNOLOGIES CORP ,  CHUANG SUE-LI ,  DONG YUAN ,  HINGORANI SANJAY S ,  PRASAD DILIP

    Inventor： CHUANG SUE-LI ,  DONG YUAN ,  HINGORANI SANJAY S ,  PRASAD DILIP

    IPC: F01D5/14 ,  F01D5/12 ,  F02C7/00

    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，所述翼型包括由压力侧和吸力侧连接的前缘和后缘，以提供沿径向方向延伸至尖端的外部翼型表面。 外部翼型表面基本上与由表1中列出的一组笛卡尔坐标描述的翼型的多个横截面轮廓形成。笛卡尔坐标由通过局部轴向弦伸缩的轴向坐标提供。 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度位置处的前缘和后缘之间的翼型的宽度。

    ACOUSTIC TREATMENT TO MITIGATE FAN NOISE
    2.
    发明申请
    ACOUSTIC TREATMENT TO MITIGATE FAN NOISE 审中-公开
    声音治疗减轻风扇噪音

    公开(公告)号：WO2014189572A3

    公开(公告)日：2015-01-08

    申请号：PCT/US2014017016

    申请日：2014-02-19

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： TOPOL DAVID A ,  MORIN BRUCE L ,  PRASAD DILIP ,  OUELLETTE THOMAS J

    IPC: F02C7/045 ,  F01D25/04

    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δ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。

    ROTOR WITH FLATTENED EXIT PRESSURE PROFILE
    3.
    发明专利
    ROTOR WITH FLATTENED EXIT PRESSURE PROFILE 未知

    公开(公告)号：SG11201403867QA

    公开(公告)日：2014-09-26

    申请号：SG11201403867Q

    申请日：2013-01-11

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： BALTAS CONSTANTINE ,  PRASAD DILIP ,  GALLAGHER EDWARD J

    IPC: F01D5/14

    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.

    DUCT FOR REDUCING SHOCK RELATED NOISE
    4.
    发明专利
    DUCT FOR REDUCING SHOCK RELATED NOISE 未知

    公开(公告)号：CA2562452A1

    公开(公告)日：2007-05-04

    申请号：CA2562452

    申请日：2006-10-03

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： FEIEREISEN JOHN MICHAEL ,  PRASAD ANIL ,  PRASAD DILIP

    IPC: F16L55/033 ,  F01D9/02 ,  F02C7/24 ,  F02K1/82

    Abstract: A duct 26 has circumferentially distributed features capable of scattering acoustic energy associated with fluid dynamic shocks 34 extending in a shock orientation direction D. Each feature is oriented, over at least a portion of its length, substantially perpendicular to the shock orientation direction. The features may be splices 42 used to connect segments of an acoustic liner 30, partitions 56 in a stability enhancing casing treatment 32, or other features capable of scattering acoustic energy associated with shocks.

    ROTOR WITH FLATTENED EXIT PRESSURE PROFILE
    6.
    发明公开
    ROTOR WITH FLATTENED EXIT PRESSURE PROFILE 审中-公开
    转子带有扁平输出压力PROFILE

    公开(公告)号：EP2807343A4

    公开(公告)日：2015-10-07

    申请号：EP13741350

    申请日：2013-01-11

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： BALTAS CONSTANTINE ,  PRASAD DILIP ,  GALLAGHER EDWARD J

    IPC: F01D5/14

    CPC classification number: F01D5/141 ,  F05D2240/30 ,  F05D2240/301 ,  F05D2240/304 ,  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.

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