公开(公告)号：US20150118064A1

公开(公告)日：2015-04-30

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

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.

Abstract translation: 机翼具有主体，其包括邻接压力侧和吸力侧的前缘和后缘，以提供外部翼型表面。 冷却通道在径向方向上从根部延伸到尖端。 后缘冷却通道将冷却通道与后缘相互连接。 后缘冷却通道包括不同尺寸的第一和第二基座，其相对于具有相同尺寸的基座并且相对于不同尺寸的基座以重复图案布置。

公开(公告)号：US10822952B2

公开(公告)日：2020-11-03

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 ,  F01D5/30 ,  F01D5/18 ,  F01D5/12

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.

公开(公告)号：US10227875B2

公开(公告)日：2019-03-12

申请号：US14766190

申请日：2014-02-07

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Scott D. Lewis ,  Brandon M. Rapp ,  Jeffrey S. Beattie ,  Matthew Andrew Hough ,  Bret M. Teller ,  Jeffrey Michael Jacques ,  Max Asterlin

IPC: F01D5/18 ,  F01D11/08 ,  F23R3/00 ,  F23R3/04 ,  F01D9/06 ,  F01D25/12 ,  F23R3/06 ,  F01D9/02 ,  F23R3/02

Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a platform that axially extends between a leading edge and a trailing edge, circumferentially extends between a first mate face and a second mate face, and includes a gas path surface and a non-gas path surface. The component defines at least one cavity that extends at least partially inside of the component. A first plurality of cooling holes extends from the at least one cavity to at least one of the first mate face and the second mate face and a second plurality of cooling holes extends from either the at least one cavity or the non-gas path surface to the gas path surface.

公开(公告)号：US10226814B2

公开(公告)日：2019-03-12

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 ,  B22D27/04 ,  B22C9/10 ,  C30B29/52 ,  B22D25/02 ,  F01D5/18 ,  F01D9/04 ,  C30B11/00 ,  F01D5/28 ,  F02C3/04

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.

公开(公告)号：US20160222809A1

公开(公告)日：2016-08-04

申请号：US15021945

申请日：2014-08-21

Applicant: UNITED TECHNOLOGIES CORPORATION

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

IPC: F01D11/00

CPC classification number: F01D11/006 ,  F01D5/22 ,  F05D2250/181 ,  F05D2250/182 ,  F05D2250/183 ,  F05D2250/75 ,  F05D2260/22141

Abstract: A gas turbine engine includes a turbine section. The turbine section includes a disk that is rotatable about an axis. A plurality of turbine blades are mounted around a periphery of the disk, and a plurality of seals are arranged between the turbine blades and the periphery of the disk. Each of the seals includes, with respect to the axis, a radially outer surface and a radially inner surface. The radially inner surface includes a plurality of protrusions.

Abstract translation: 燃气涡轮发动机包括涡轮部分。 涡轮机部分包括可围绕轴线旋转的盘。 多个涡轮机叶片围绕盘的周边安装，并且多个密封件布置在涡轮机叶片与盘周边之间。 每个密封件相对于轴线包括径向外表面和径向内表面。 径向内表面包括多个突起。

公开(公告)号：US20160177782A1

公开(公告)日：2016-06-23

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 ,  F01D9/04 ,  F04D29/38 ,  F04D29/32 ,  F04D29/54 ,  F04D29/58 ,  F01D5/12 ,  F01D11/08

CPC classification number: F01D25/12 ,  F01D5/12 ,  F01D5/187 ,  F01D9/041 ,  F01D11/006 ,  F01D11/08 ,  F04D29/324 ,  F04D29/38 ,  F04D29/542 ,  F04D29/582 ,  F05D2220/32 ,  F05D2230/21 ,  F05D2230/211 ,  F05D2230/30 ,  F05D2240/81 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2260/205 ,  F05D2260/2212 ,  F05D2300/13 ,  F05D2300/20 ,  Y02T50/676

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.

Abstract translation: 本公开的一个示例性实施例涉及包括部件的燃气涡轮发动机。 该部件包括在其圆周侧上具有接合面的平台。 平台包括配置成将流体传送到配合面的芯通道。

公开(公告)号：US20160032727A1

公开(公告)日：2016-02-04

申请号：US14775179

申请日：2014-03-13

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Matthew A. Hough ,  Jeffrey S. Beattie

IPC: F01D5/14

CPC classification number: F01D5/141 ,  F01D5/147 ,  F01D5/22 ,  F01D5/3007 ,  F05D2220/30 ,  F05D2240/30 ,  F05D2240/80 ,  F05D2250/14 ,  F05D2250/711 ,  F05D2250/712 ,  F05D2260/941

Abstract: A rotor blade for a turbine engine includes an airfoil that is connected to a base. The base includes a platform, a neck and a fillet. The fillet extends along at least a portion of an intersection between the platform and the neck. The fillet has a radius that substantially continuously changes as the fillet extends from the platform to the neck.

Abstract translation: 用于涡轮发动机的转子叶片包括连接到基座的翼型件。 底座包括平台，颈部和圆角。 圆角沿平台和颈部之间的交叉点的至少一部分延伸。 圆角的半径随着圆角从平台延伸到颈部而基本上连续变化。

公开(公告)号：US20160003607A1

公开(公告)日：2016-01-07

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 ,  G01M13/00

CPC classification number: G01B11/00 ,  G01B11/24 ,  G01B21/20 ,  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.

Abstract translation: 提供了一种用于使用可固化材料和检查系统检查部件的至少一个孔的方法。 至少一部分可固化材料被注入孔中。 可固化材料符合孔的至少一部分并随后固化并形成孔的至少一部分的模具。 将模具从孔中取出。 将模具的几何形状的至少一部分与使用检查系统的孔的参考模型的几何形状的至少一部分进行比较。