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    AIRFOIL WITH VARIABLE PROFILE RESPONSIVE TO THERMAL CONDITIONS
    14.
    发明申请
    AIRFOIL WITH VARIABLE PROFILE RESPONSIVE TO THERMAL CONDITIONS 审中-公开
    具有适用于热条件的变体型材的气翼

    公开(公告)号：US20170002666A1

    公开(公告)日：2017-01-05

    申请号：US15267186

    申请日：2016-09-16

    Applicant: United Technologies Corporation

    Inventor： Richard K. Hayford ,  Paul M. Lutjen

    IPC: F01D5/28 ,  F02C3/04

    CPC classification number: F01D5/28 ,  F01D5/148 ,  F02C3/04 ,  F05D2220/32 ,  F05D2300/10 ,  F05D2300/50212 ,  Y02T50/673

    Abstract: An airfoil includes an airfoil body having a first section and a second section that differ in coefficient of thermal expansion by at least 10% and that each have a through-thickness that is 20% or greater than a through-thickness of the airfoil body. The second section is arranged in thermomechanical juxtaposition with the first section such that the first section and the second section cooperatively thermomechanically control a profile of the airfoil body responsive to varying thermal conditions.

    Abstract translation: 翼型件包括具有第一部分和第二部分的翼型本体，所述第一部分和第二部分的热膨胀系数不同于至少10％，并且每个部分的贯穿厚度为翼型体的贯穿厚度的20％或更大。 第二部分与第一部分以热机械并置布置，使得第一部分和第二部分协调地热机械地响应于变化的热条件来控制翼型体的轮廓。

    VANE SEAL SYSTEM HAVING SPRING POSITIVELY LOCATING SEAL MEMBER IN AXIAL DIRECTION
    15.
    发明申请
    VANE SEAL SYSTEM HAVING SPRING POSITIVELY LOCATING SEAL MEMBER IN AXIAL DIRECTION 审中-公开
    具有弹簧位置密封构件的VANE密封系统在轴向方向

    公开(公告)号：US20160215637A1

    公开(公告)日：2016-07-28

    申请号：US15026011

    申请日：2014-09-23

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Mark J. Rogers ,  Carl S. Richardson ,  Richard K. Hayford ,  Kenneth E. Carman ,  Jonathan J. Earl

    IPC: F01D11/00

    CPC classification number: F01D11/001 ,  F01D9/041 ,  F05D2260/38

    Abstract: A vane seal system includes a non-rotatable vane segment that has an airfoil with a pocket at one end thereof. The pocket spans in an axial direction between forward and trailing sides, with respect to the airfoil, and in a lateral direction between open lateral sides. A seal member extends in the pocket. The seal member includes a seal element and at least one spring portion that is configured to positively locate the seal member in the axial direction in the pocket. A method for positioning the seal member in a vane seal system includes positively locating the seal member in the axial direction in the pocket using the spring portion.

    Abstract translation: 叶片密封系统包括不可旋转的叶片段，其具有在其一端具有口袋的翼型件。 口袋相对于翼型件在前后两侧之间的轴向方向上跨过敞开的侧边之间的横向方向。 密封件在口袋中延伸。 密封构件包括密封元件和至少一个弹簧部分，其构造成沿着轴向方向将密封构件正确定位在口袋中。 用于将密封构件定位在叶片密封系统中的方法包括使用弹簧部分将密封构件沿轴向方向定位在凹穴中。

    Vane seal system and seal therefor
    16.
    发明授权
    Vane seal system and seal therefor 有权

    公开(公告)号：US10808563B2

    公开(公告)日：2020-10-20

    申请号：US15026709

    申请日：2014-09-09

    Applicant: United Technologies Corporation

    Inventor： Mark J. Rogers ,  Carl S. Richardson ,  Richard K. Hayford ,  Kenneth E. Carman ,  Jonathan J. Earl

    IPC: F01D11/00 ,  F01D11/08 ,  F01D25/04 ,  F01D9/04

    Abstract: A vane seal system includes a first non-rotatable vane segment that has a first airfoil with a first pocket at one end thereof. A second non-rotatable vane segment includes a second airfoil with a second pocket at one end thereof spaced by a gap from the first pocket. A seal member spans across the gap and extends in the first pocket and the second pocket. The seal member includes a seal element and at least one spring portion configured to positively locate the seal member in a sealing direction. Also disclosed is a seal for a vane seal system and a method related thereto for damping relative movement between a first pocket and a second pocket.

    Mistuned concentric airfoil assembly and method of mistuning same
    17.
    发明授权
    Mistuned concentric airfoil assembly and method of mistuning same 有权

    公开(公告)号：US10767486B2

    公开(公告)日：2020-09-08

    申请号：US16106221

    申请日：2018-08-21

    Applicant: United Technologies Corporation

    Inventor： Richard K. Hayford ,  Steven J. Ford

    IPC: F01D5/14 ,  F01D5/02 ,  F01D5/22 ,  F01D25/06

    Abstract: An airfoil assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, an annular shroud having a radially inner face and a radially outer face opposing the radially inner face, a radially inner array of airfoils extending from the radially inner face, and a radially outer array of airfoils extending from the radially outer face. The radially inner array of airfoils are configured to guide flow within a radially inner bypass flow passage, the radially inner bypass flow passage bypassing and being radially outward of a compressor section. At least one, but fewer than each, airfoil of the radially inner array of airfoils is circumferentially aligned with a corresponding airfoil in the radially outer array of airfoils, and the remaining airfoils in the radially inner array of airfoils are misaligned with the airfoils of the radially outer array of airfoils. A method of reducing a vibratory response of airfoils is also disclosed.

    PLANETARY GEAR SYSTEM FOR TURBOMACHINE
    18.
    发明申请
    PLANETARY GEAR SYSTEM FOR TURBOMACHINE 审中-公开

    公开(公告)号：US20200182159A1

    公开(公告)日：2020-06-11

    申请号：US16730466

    申请日：2019-12-30

    Applicant: United Technologies Corporation

    Inventor： Ken F. Blaney ,  Todd M. LaPierre ,  Richard K. Hayford

    IPC: F02C7/36 ,  F16H57/028 ,  F16H57/025 ,  F16H1/46 ,  F02C3/107 ,  F02K3/06

    Abstract: A planetary gear system for a turbomachine includes a forward planetary gear assembly including a plurality of forward planet gears meshed to a forward sun gear disposed on a power shaft and a forward ring gear meshed to the forward planet gears and an aft planetary gear assembly aft of the forward planetary assembly including a plurality of aft planet gears meshed to an aft sun gear disposed on the power shaft and an aft ring gear meshed to the aft planet gears. The system also includes a gear housing disposed between the forward planetary gear assembly and the aft planetary gear assembly. The gear housing includes a stationary carrier, wherein the forward and aft planet gears are rotatably mounted to the stationary carrier, and a mount extending radially from the stationary carrier that is connectable to a stationary portion of the turbomachine.

    Planetary gear system for turbomachine
    19.
    发明授权
    Planetary gear system for turbomachine 有权

    公开(公告)号：US10519872B2

    公开(公告)日：2019-12-31

    申请号：US15688251

    申请日：2017-08-28

    Applicant: United Technologies Corporation

    Inventor： Ken F. Blaney ,  Todd M. LaPierre ,  Richard K. Hayford

    IPC: F16H57/025 ,  F02C7/36 ,  F02K3/06 ,  F02C3/107 ,  F16H1/46 ,  F16H57/028

    Abstract: A planetary gear system for a turbomachine includes a forward planetary gear assembly including a plurality of forward planet gears meshed to a forward sun gear disposed on a power shaft and a forward ring gear meshed to the forward planet gears and an aft planetary gear assembly aft of the forward planetary assembly including a plurality of aft planet gears meshed to an aft sun gear disposed on the power shaft and an aft ring gear meshed to the aft planet gears. The system also includes a gear housing disposed between the forward planetary gear assembly and the aft planetary gear assembly. The gear housing includes a stationary carrier, wherein the forward and aft planet gears are rotatably mounted to the stationary carrier, and a mount extending radially from the stationary carrier that is connectable to a stationary portion of the turbomachine.

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