公开(公告)号：US10533453B2

公开(公告)日：2020-01-14

申请号：US14910551

申请日：2014-08-05

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Matthew Andrew Hough ,  Jeffrey S. Beattie ,  Tracy A. Propheter-Hinckley ,  San Quach

IPC: F01D25/12 ,  F01D5/18 ,  F01D5/12 ,  F01D9/04 ,  F01D11/08 ,  F04D29/32 ,  F04D29/38 ,  F04D29/54 ,  F04D29/58 ,  F01D11/00

Abstract: One exemplary embodiment of this disclosure relates to a gas turbine engine including a component. The component includes a platform having a mateface on a circumferential side thereof. The platform including a core passageway configured to communicate fluid to the mateface.

公开(公告)号：US10203196B2

公开(公告)日：2019-02-12

申请号：US14770753

申请日：2014-02-25

Applicant: United Technologies Corporation

Inventor： Gordon M. Reed ,  James Romanelli ,  James M. Koonankeil ,  Kevin J. Klinefelter ,  Markus W. Fritch ,  Kenneth J. Hollman ,  Jeffrey S. Beattie

IPC: G01B11/00 ,  G01B21/20 ,  G01B11/24 ,  G01M13/00

Abstract: A method is provided for inspecting at least one aperture of a component with curable material and an inspection system. At least a portion of the curable material is injected into the aperture. The curable material conforms to at least a portion the aperture and subsequently cures and forms a mold of at least a portion of the aperture. The mold is removed from the aperture. At least a portion of a geometry of the mold is compared to at least a portion of a geometry of a reference model for the aperture using the inspection system.

公开(公告)号：US10100648B2

公开(公告)日：2018-10-16

申请号：US14961395

申请日：2015-12-07

Applicant: United Technologies Corporation

Inventor： David A. Niezelski ,  Joshua D. Winn ,  Jeffrey S. Beattie

IPC: F01D5/22 ,  F01D5/26 ,  F01D5/30 ,  F01D11/00 ,  F16F15/04

Abstract: Aspects of the disclosure are directed to a damper configured to be located in a cavity formed between first and second bases configured to seat respective first and second airfoils, the damper having a first face and a second face, where an aspect ratio between the first face and the second face ensures that the damper is installed in the cavity in accordance with a predetermined orientation.

公开(公告)号：US09938837B2

公开(公告)日：2018-04-10

申请号：US14390496

申请日：2013-03-12

Applicant: United Technologies Corporation

Inventor： Jeffrey R. Levine ,  Jeffrey S. Beattie ,  Malcolm C. Staddon

IPC: F01D5/18 ,  B22C9/10

CPC classification number: F01D5/188 ,  B22C9/103 ,  B22C9/108 ,  F01D5/187 ,  F05D2200/33 ,  F05D2230/211 ,  F05D2260/22141 ,  F05D2260/607 ,  F05D2300/13 ,  Y02E10/721

Abstract: An airfoil has a body that includes leading and trailing edges that adjoin pressure and suction sides to provide an exterior airfoil surface. A cooling passage extends in a radial direction from a root to a tip. A trailing edge cooling passage interconnects the cooling passage to the trailing edge. The trailing edge cooling passage includes first and second pedestals of different sizes that are arranged in a repeating pattern with respect to pedestals of the same size and with respect to pedestals of different sizes.

公开(公告)号：US09546556B2

公开(公告)日：2017-01-17

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。

公开(公告)号：US20160222787A1

公开(公告)日：2016-08-04

申请号：US15021060

申请日：2014-09-17

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Jeffrey S. Beattie ,  Jason D. Himes ,  Matthew Andrew Hough ,  Christopher Corcoran

IPC: F01D5/08 ,  F01D5/12 ,  F01D5/30

Abstract: An assembly according to an exemplary aspect of the present disclosure includes, among other things, a disk, a cover plate providing a cavity at a first axial side of the disk, a passageway including an inlet provided by a notch in at least one of the disk and the cover plate in fluid communication with the cavity, and the passageway extending from the inlet to an exit provided at a second axial side of the disk opposite the first axial side, the exit in fluid communication with the inlet, and the passageway configured to provide fluid flow from the cavity to the exit.

Abstract translation: 根据本公开的示例性方面的组件包括盘，在盘的第一轴向侧提供空腔的盖板，包括由至少一个中的至少一个中的凹口提供的入口的通道 盘和盖板与空腔流体连通，并且从入口延伸到设置在与第一轴向侧相对的盘的第二轴向侧处的出口的通道，与入口流体连通的出口和配置的通道 以提供从空腔到出口的流体流动。

公开(公告)号：US20160001356A1

公开(公告)日：2016-01-07

申请号：US14769803

申请日：2014-03-11

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Max Asterlin ,  Jeffrey S. Beattie ,  John R. Gunn

IPC: B22D15/00 ,  F01D5/28 ,  B22D27/04 ,  F01D9/04 ,  B22D25/02 ,  F02C3/04 ,  F01D5/18

CPC classification number: B22D15/00 ,  B22C9/10 ,  B22D25/02 ,  B22D27/04 ,  B22D27/045 ,  C30B11/00 ,  C30B29/52 ,  F01D5/18 ,  F01D5/187 ,  F01D5/282 ,  F01D9/041 ,  F02C3/04 ,  F05D2220/30 ,  F05D2230/21 ,  F05D2230/211 ,  F05D2260/20 ,  F05D2260/204 ,  F05D2300/607 ,  F05D2300/608 ,  Y02T50/676

Abstract: A cast component includes a cast body that has a single crystal microstructure and an internal corner bounding an internal cavity. The single crystal microstructure defines a critical internal residual stress with respect to investment casting of the cast body using a refractory metal core beyond which the single crystal microstructure recrystallizes under a predetermined condition. The internal corner has a corner radius that is greater than a critical corner radius below which an amount of internal residual stress in the single crystal microstructure exceeds the critical internal residual stress. The internal cavity includes a cross section less than about 20 mils near the corner radius.

Abstract translation: 铸造组件包括具有单晶微结构的铸造体和包围内腔的内角。 单晶微结构定义了使用难熔金属芯相对于铸造体的熔模铸造的关键内部残余应力，超临界内的单晶微结构在预定条件下重结晶。 内角具有大于临界角半径的角半径，低于该半径时，单晶微结构中的内部残余应力的量超过临界内部残余应力。 内腔包括在拐角半径附近小于约20密耳的横截面。

公开(公告)号：US10563525B2

公开(公告)日：2020-02-18

申请号：US15038536

申请日：2014-11-05

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Matthew Andrew Hough ,  Christopher Corcoran ,  Jeffrey S. Beattie

IPC: F01D5/30 ,  F01D25/00

Abstract: A gas turbine engine component comprises a blade having a leading edge and a trailing edge. The blade is mounted to a disc and configured for rotation about an axis. A platform supports the blade, and has a fore edge portion at the leading edge and an aft edge portion at the trailing edge. At least one of the fore edge portion and aft edge portion includes a mouth portion defined by an inner wing and an outer wing spaced radially outward of the inner wing. At least one coverplate is retained against the disc by the inner wing. A gas turbine engine is also disclosed.

公开(公告)号：US20190316475A1

公开(公告)日：2019-10-17

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.

公开(公告)号：US10364682B2

公开(公告)日：2019-07-30

申请号：US15021991

申请日：2014-08-28

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 from the platform, a first cooling core that extends at least partially inside the airfoil, a second cooling core inside of the platform and a first cooling hole that extends between a mate face of the platform and the second cooling core.