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    Platform cooling core for a gas turbine engine rotor blade
    1.
    发明授权
    Platform cooling core for a gas turbine engine rotor blade 有权

    公开(公告)号：US10907481B2

    公开(公告)日：2021-02-02

    申请号：US16427870

    申请日：2019-05-31

    Applicant: United Technologies Corporation

    Inventor： Matthew Andrew Hough ,  Jeffrey S. Beattie

    IPC: F01D5/18

    Abstract: A rotor blade according to an exemplary aspect of the present disclosure includes, among other things, a platform, an airfoil that extends radially from the platform, a first cooling core that extends at least partially inside the airfoil, a second cooling core inside of the platform, a first cooling hole that extends circumferentially between a mate face of the platform and the second cooling core, a second cooling hole that extends between a gas path surface of the platform and the second cooling core, the second cooling core radially disposed between the gas path surface and a non-gas path surface, and the second cooling core circumferentially disposed between the first cooling core and the mate face. A method of cooling a blade is also disclosed.

    Gas turbine engine with disk having periphery with protrusions
    2.
    发明授权
    Gas turbine engine with disk having periphery with protrusions 有权

    公开(公告)号：US10253642B2

    公开(公告)日：2019-04-09

    申请号：US15021944

    申请日：2014-08-21

    Applicant: United Technologies Corporation

    Inventor： Matthew Andrew Hough ,  Jeffrey S. Beattie

    IPC: F01D5/14 ,  F01D11/00 ,  F01D5/08 ,  F01D5/30 ,  F01D11/02 ,  F01D25/12

    Abstract: A gas turbine engine includes a turbine section that has a disk rotatable about an axis. The disk has circumferentially-spaced blade mounting features and radially outer rim surfaces extending circumferentially between the blade mounting features. Turbine blades are mounted circumferentially around the disk in the blade mounting features. Seals are arranged radially outwards of the disk adjacent the radially outer rim surfaces such that there are respective passages between the seals and the radially outer rim surfaces. The radially outer rim surfaces include radially-extending protrusions that extend into the respective passages.

    Disk outer rim seal
    3.
    发明授权
    Disk outer rim seal 有权

    公开(公告)号：US10167722B2

    公开(公告)日：2019-01-01

    申请号：US15021374

    申请日：2014-09-10

    Applicant: United Technologies Corporation

    Inventor： Matthew Andrew Hough ,  Jeffrey S. Beattie

    IPC: F01D5/08 ,  F01D5/30 ,  F01D5/12 ,  F01D11/00

    Abstract: A turbine section comprises a rotor, blade and rim seal. The rotor comprises a rim defining an outer diameter surface, and a slot in the outer diameter surface. The blade comprises an airfoil, a platform surrounding the airfoil, a shank extending from the platform, a root extending from the shank for connecting to the slot, and a nub extending from the shank beneath the platform. The rim seal is disposed between the outer diameter surface and the nub. A method for cooling an outer diameter of a rotor disk comprises bleeding cooling air in a gas turbine engine, passing the flow of cooling air through a cover plate that retains a seal plate against the rotor disk, leaking the cooing air between a rotor disk rim and the seal plate, and guiding the cooling air across an outer diameter surface of the rotor disk rim utilizing a rim seal.

    DISK OUTER RIM SEAL
    4.
    发明申请
    DISK OUTER RIM SEAL 审中-公开
    DISK OUTER RIM密封

    公开(公告)号：US20160222788A1

    公开(公告)日：2016-08-04

    申请号：US15021374

    申请日：2014-09-10

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Matthew Andrew Hough ,  Jeffrey S. Beattie

    IPC: F01D5/08 ,  F01D5/30 ,  F01D11/00 ,  F01D5/12

    CPC classification number: F01D5/082 ,  F01D5/081 ,  F01D5/084 ,  F01D5/085 ,  F01D5/12 ,  F01D5/3007 ,  F01D5/3015 ,  F01D11/006 ,  F05D2220/32 ,  F05D2260/232

    Abstract: A turbine section comprises a rotor, blade and rim seal. The rotor comprises a rim defining an outer diameter surface, and a slot in the outer diameter surface. The blade comprises an airfoil, a platform surrounding the airfoil, a shank extending from the platform, a root extending from the shank for connecting to the slot, and a nub extending from the shank beneath the platform. The rim seal is disposed between the outer diameter surface and the nub. A method for cooling an outer diameter of a rotor disk comprises bleeding cooling air in a gas turbine engine, passing the flow of cooling air through a cover plate that retains a seal plate against the rotor disk, leaking the cooing air between a rotor disk rim and the seal plate, and guiding the cooling air across an outer diameter surface of the rotor disk rim utilizing a rim seal.

    Abstract translation: 涡轮机部分包括转子，叶片和轮缘密封件。 转子包括限定外径表面的边缘和外径表面中的狭槽。 叶片包括翼型件，围绕翼型的平台，从平台延伸的柄部，从柄部延伸的用于连接到狭槽的根部以及从平台下方的柄延伸的突出部。 边缘密封件设置在外径表面和凸起之间。 用于冷却转子盘的外径的方法包括使燃气涡轮发动机中的冷却空气渗出，使冷却空气流通过将密封板保持在转子盘上的盖板，使冷凝空气在转子盘轮圈 和密封板，并且利用边缘密封件将冷却空气引导到转子盘边缘的外径表面。

    Seal damper with improved retention
    6.
    发明授权
    Seal damper with improved retention 有权

    公开(公告)号：US10247023B2

    公开(公告)日：2019-04-02

    申请号：US14429089

    申请日：2013-03-14

    Applicant: United Technologies Corporation

    Inventor： Jeffrey S. Beattie ,  Jeffrey Michael Jacques

    IPC: F01D5/22 ,  F01D5/26 ,  F01D11/00

    Abstract: A seal damper system includes a plurality of circumferentially spaced blades that each include a platform and an airfoil that extends radially outwardly from the platform. A pocket is arranged circumferentially intermediate the blades and radially inwardly of the platform. A seal damper is arranged in the pocket. The seal damper includes a base section that extends along an axial dimension from a first axial end to an opposing second axial end. The base section joins a first arm that extends radially inwardly from the first axial end and a second arm that extends radially inwardly from the second axial end. The first arm includes a free end having a pair of spaced apart shoulders.

    SEAL DAMPER WITH IMPROVED RETENTION
    9.
    发明申请
    SEAL DAMPER WITH IMPROVED RETENTION 审中-公开
    具有改进保持性的密封阻尼器

    公开(公告)号：US20150226077A1

    公开(公告)日：2015-08-13

    申请号：US14429089

    申请日：2013-03-14

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Jeffrey S. Beattie ,  Jeffrey Michael Jacques

    IPC: F01D11/00 ,  F01D5/22

    CPC classification number: F01D11/006 ,  F01D5/22 ,  F01D5/26 ,  F01D11/008

    Abstract: A seal damper system includes a plurality of circumferentially spaced blades that each include a platform and an air-foil that extends radially outwardly from the platform. A pocket is arranged circumferentially intermediate the blades and radially inwardly of the platform. A seal damper is arranged in the pocket. The seal damper includes a base section that extends along an axial dimension from a first axial end to an opposing second axial end. The base section joins a first arm that extends radially inwardly from the first axial end and a second arm that extends radially inwardly from the second axial end. The first arm includes a free end having a pair of spaced apart shoulders.

    Abstract translation: 密封阻尼器系统包括多个周向间隔开的叶片，每个叶片包括平台和从平台径向向外延伸的空气箔片。 一个口袋沿圆周方向布置在刀片和径向向内的平台上。 密封阻尼器布置在口袋中。 密封阻尼器包括基部，该基部沿轴向尺寸从第一轴向端延伸到相对的第二轴向端。 基部接合从第一轴向端径向向内延伸的第一臂和从第二轴向端径向向内延伸的第二臂。 第一臂包括具有一对间隔开的肩部的自由端。

    TURBINE BLADE ROOT PROFILE
    10.
    发明申请
    TURBINE BLADE ROOT PROFILE 有权
    涡轮叶片轮廓

    公开(公告)号：US20140083114A1

    公开(公告)日：2014-03-27

    申请号：US13626937

    申请日：2012-09-26

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Jeffrey S. Beattie ,  Jeffrey Michael Jacques

    IPC: F01D5/30 ,  F01D5/18

    CPC classification number: F01D5/30 ,  F01D5/18 ,  F01D5/3007

    Abstract: A turbine blade for a gas turbine engine includes an airfoil that extends in a first radial direction from a platform. A root extends from the platform in a second radial direction and has opposing lateral sides that provide a firtree-shaped contour. The contour includes first, second and third lobes on each of the lateral sides and that tapers relative to the radial direction away from the platform. The first, second and third lobes each provide contact surfaces arranged at about 45° relative to the radial direction. A contact plane on each lateral side at an angle of about 11° relative to the radial direction defining a contact point on each of the contact surfaces. The first, second and third lobes each include first, second and third grooves that are substantially aligned with one another along an offset plane spaced a uniform offset distance from the contact plane.

    Abstract translation: 用于燃气涡轮发动机的涡轮机叶片包括从平台沿第一径向方向延伸的翼型件。 根部在第二径向方向上从平台延伸并且具有相对的侧向侧面，该侧面侧面提供保持曲面的轮廓。 轮廓包括在每个侧面上的第一，第二和第三凸角，并且相对于远离平台的径向方向逐渐变细。 第一，第二和第三叶片各自提供相对于径向方向布置成大约45°的接触表面。 在每个侧面上的接触平面相对于径向方向以约11°的角度限定每个接触表面上的接触点。 第一，第二和第三凸耳各自包括第一，第二和第三凹槽，其沿着与接触平面间隔开均匀偏移距离的偏移平面彼此基本对齐。

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