公开(公告)号：US20210102468A1

公开(公告)日：2021-04-08

申请号：US16590925

申请日：2019-10-02

Applicant: United Technologies Corporation

Inventor： Michael G. McCaffrey ,  Karl A. Mentz ,  Christopher King ,  Stephen D. Doll ,  Aurelia Ledbetter

IPC: F01D5/28

Abstract: A process for manufacturing a composite rotor blade includes manufacturing an oversized root region of a root region of a composite rotor blade; fixturing the CMC blade into a machining fixture at a primary Y and Z axis datum located at an attachment fillet radii of the root region; machining V-notches into the oversized root region to form a Y′ and Z′ axis datum of a sacrificial datum system in relation to the primary Y and Z axis datum; applying an oversized coating layer over the attachment fillet radii of the root region; fixturing the CMC blade into a machining fixture at the Y′ and Z′ axis datum of the sacrificial datum system; machining the oversized coating layer to a machined coating layer forming a Y″ and Z″ axis datum with respect to the Y′ and Z′ axis datum of the sacrificial datum system; fixturing the CMC blade into a machining fixture at the Y″ and Z″ axis datum; and machining off the sacrificial datum system removing the V-notches.

公开(公告)号：US10323569B2

公开(公告)日：2019-06-18

申请号：US15283837

申请日：2016-10-03

Applicant: United Technologies Corporation

Inventor： Christopher King

IPC: B22C9/10 ,  F02C3/04 ,  F02C7/12

Abstract: Core assemblies and methods for manufacturing components of gas turbine engines include a first core body having a first trunk configured to attach to a first location of a cavity core structure, a first branch extending from the first trunk and configured to form a first portion of a first cooling circuit, the first branch having a first joining surface, and a second core body having a second trunk configured to attach to a second location of a cavity core structure, a first branch of the second core body extending from the second trunk and configured to form a first portion of a second cooling circuit in the component. The first branches of the core bodies joined to form a junction. The junction defines a merger of the first cooling circuit and the second cooling circuit proximate to an exit of the first and second cooling circuits.

公开(公告)号：US10247011B2

公开(公告)日：2019-04-02

申请号：US14923553

申请日：2015-10-27

Applicant: United Technologies Corporation

Inventor： San Quach ,  Christopher King ,  Thomas N. Slavens

IPC: F01D5/18 ,  F01D5/02 ,  F01D9/04 ,  F02C3/04 ,  F02C7/18 ,  F23R3/00 ,  F01D11/08 ,  F01D25/12

Abstract: A cooling circuit for a gas turbine engine comprises a gas turbine engine component having a body with at least one internal cavity defined by a cavity wall. A plurality of cooling holes formed within the cavity wall, wherein each cooling hole is defined by a length extending from a cooling hole inlet to a cooling hole outlet, and wherein the cooling holes are positioned relative to each other such that a minimum allowable ligament distance is maintained between adjacent cooling holes along the entire length of each cooling hole. A gas turbine engine and a method of forming a cooling circuit for a gas turbine engine are also disclosed.

公开(公告)号：US20180252108A1

公开(公告)日：2018-09-06

申请号：US15972475

申请日：2018-05-07

Applicant: United Technologies Corporation

Inventor： Christopher King

IPC: F01D5/18 ,  B22C9/10 ,  F23R3/00 ,  F02C7/18 ,  F01D25/12 ,  F01D11/08 ,  F01D9/04 ,  F01D5/14 ,  B23H9/14 ,  B22D25/02 ,  B23K26/382

CPC classification number: F01D5/186 ,  B22C9/10 ,  B22D25/02 ,  B23H9/14 ,  B23K26/382 ,  F01D5/147 ,  F01D9/041 ,  F01D11/08 ,  F01D25/12 ,  F02C7/18 ,  F05D2220/32 ,  F05D2230/12 ,  F05D2230/13 ,  F05D2230/21 ,  F05D2230/30 ,  F05D2260/202 ,  F23R3/002 ,  Y02T50/676

Abstract: A core for gas turbine engine component comprises a body extending between first and second ends to define a length, and extending between first and second edges to define a width. A plurality of core extensions are formed as part of the body. The plurality of core extensions are positioned to be staggered relative to each other such that at least two adjacent core extensions are variable relative to each other in at least one dimension. A gas turbine engine component is also disclosed.

公开(公告)号：US20170089206A1

公开(公告)日：2017-03-30

申请号：US14871456

申请日：2015-09-30

Applicant: United Technologies Corporation

Inventor： San Quach ,  Steven Bruce Gautschi ,  Matthew A. Devore ,  Scott D. Lewis ,  Matthew S. Gleiner ,  Christopher King ,  Christopher Corcoran ,  David Donald Chapdelaine

IPC: F01D5/18

CPC classification number: F01D5/187 ,  F01D5/186 ,  F01D5/20 ,  F05D2220/32 ,  F05D2240/307 ,  F05D2260/202 ,  Y02T50/673 ,  Y02T50/676

Abstract: An airfoil for use in a gas turbine engine is provided. The airfoil having: a pressure surface and a suction surface each extending axially from a leading edge to a trailing edge of the airfoil, at least one of the pressure surface, the suction surface, the leading edge and the trailing edge terminating at an edge of a tip section of the airfoil; a plurality of internal cooling channels located within the airfoil; and at least one cooling hole in fluid communication with at least one of the plurality of internal cooling channels, wherein the at least one cooling hole is aligned with an opening or diffuser that extends directly from the at least one cooling hole and wherein the opening or diffuser is formed in and extends through the edge of the tip section of the airfoil.

公开(公告)号：US20160222792A1

公开(公告)日：2016-08-04

申请号：US14609677

申请日：2015-01-30

Applicant: United Technologies Corporation

Inventor： Christopher King

IPC: F01D5/18 ,  F01D9/04 ,  F01D11/08 ,  B22D25/02 ,  F23R3/00 ,  F02C7/18 ,  B23H9/14 ,  B23K26/382 ,  F01D5/14 ,  F01D25/12

CPC classification number: F01D5/186 ,  B22C9/10 ,  B22D25/02 ,  B23H9/14 ,  B23K26/382 ,  F01D5/147 ,  F01D9/041 ,  F01D11/08 ,  F01D25/12 ,  F02C7/18 ,  F05D2220/32 ,  F05D2230/12 ,  F05D2230/13 ,  F05D2230/21 ,  F05D2230/30 ,  F05D2260/202 ,  F23R3/002 ,  Y02T50/676

Abstract: A core for gas turbine engine component comprises a body extending between first and second ends to define a length, and extending between first and second edges to define a width. A plurality of core extensions are formed as part of the body. The plurality of core extensions are positioned to be staggered relative to each other such that at least two adjacent core extensions are variable relative to each other in at least one dimension. A gas turbine engine component is also disclosed.

Abstract translation: 用于燃气涡轮发动机部件的核心包括在第一和第二端之间延伸以限定长度并且在第一和第二边缘之间延伸以限定宽度的主体。 多个芯部延伸部形成为身体的一部分。 多个芯部延伸部被定位成相对于彼此交错，使得至少两个相邻的芯部延伸部在至少一个维度上相对于彼此是可变的。 还公开了一种燃气涡轮发动机部件。

公开(公告)号：US10156157B2

公开(公告)日：2018-12-18

申请号：US14622062

申请日：2015-02-13

Applicant: United Technologies Corporation

Inventor： Christopher King ,  Edward F. Pietraszkiewicz

IPC: F01D5/18 ,  F01D5/12 ,  F02C7/24 ,  F02C7/18 ,  F01D25/12 ,  F01D9/04

Abstract: A component for a gas turbine engine is provided. The component includes an internal cooling passage disposed within the component, and an s-shaped trip strip formed on a surface of the internal cooling passage.

公开(公告)号：US20170002663A1

公开(公告)日：2017-01-05

申请号：US14790231

申请日：2015-07-02

Applicant: United Technologies Corporation

Inventor： San Quach ,  Scott D. Lewis ,  Steven Bruce Gautschi ,  Christopher King ,  Christopher Corcoran ,  David Donald Chapdelaine

IPC: F01D5/18

CPC classification number: F01D5/20 ,  F05D2260/202 ,  Y02T50/673 ,  Y02T50/676

Abstract: A gas turbine engine airfoil includes a body that provides an exterior airfoil surface that extends in a radial direction to a tip. The exterior surface has a leading edge in a forward direction and a trailing edge in an aft direction. The tip includes a squealer pocket that has a recess surface. A cooling passage is arranged in the body. Each of the cooling holes extends from an inlet at the cooling passage to an outlet at the recessed surface. The inlet and outlet are arranged at an angle in an angular direction relative to the recessed surface. The angular direction is toward at least one of the forward and aft directions.

Abstract translation: 燃气涡轮发动机翼型件包括提供沿径向方向延伸到尖端的外部翼面表面的主体。 外表面具有向前方向的前缘和向后方的后缘。 尖端包括具有凹陷表面的尖叫口袋。 冷却通道设置在体内。 每个冷却孔从冷却通道的入口延伸到凹陷表面处的出口。 入口和出口相对于凹入表面以角度方向成一定角度布置。 角度方向朝着前后方向中的至少一个方向。

公开(公告)号：US20160251968A1

公开(公告)日：2016-09-01

申请号：US14632485

申请日：2015-02-26

Applicant: United Technologies Corporation

Inventor： San Quach ,  Ryan Alan Waite ,  Christopher King ,  Steven Bruce Gautschi

IPC: F01D5/18 ,  F23R3/00 ,  F01D11/08 ,  F01D25/30 ,  F01D5/14 ,  F01D9/04

CPC classification number: F01D5/187 ,  F01D5/147 ,  F01D9/041 ,  F01D11/08 ,  F01D25/30 ,  F05D2220/32 ,  F05D2240/122 ,  F05D2240/127 ,  F05D2240/304 ,  F05D2240/307 ,  F05D2240/35 ,  F05D2240/55 ,  F05D2260/221 ,  F05D2260/2212 ,  F05D2260/2214 ,  F23R3/002 ,  Y02T50/673 ,  Y02T50/676

Abstract: An airfoil for a gas turbine engine includes an airfoil including spaced apart pressure and suction side walls joined at leading and trailing edges to provide an exterior airfoil surface that extends in a radial direction from a platform to a tip. A cavity is provided between the pressure and suction side walls near the trailing edge. The cavity includes an interior region bounded by first and second exit regions arranged at angle relative to one another. The first and second exit regions are respectively in low and high pressure regions relative to one another. First and second pedestal groups respectively are arranged at the first and second exit regions. The second pedestal group has first and second pedestals each terminating in an end. The ends of the second pedestals extend beyond the ends of first pedestals.

Abstract translation: 用于燃气涡轮发动机的翼型件包括翼型件，其包括在前缘和后缘处连接的间隔开的压力和抽吸侧壁，以提供从平台向尖端沿径向延伸的外部翼型件表面。 在后缘附近的压力侧和吸力侧壁之间设置空腔。 空腔包括由相对于彼此成角度布置的第一和第二出射区域界定的内部区域。 第一出口区域和第二出口区域分别相对于彼此在低压区域和高压区域中。 分别在第一和第二出口区域设置第一和第二基座组。 第二基座组具有各自终止的第一和第二基座。 第二基座的端部延伸超过第一基座的端部。

公开(公告)号：US20160230563A1

公开(公告)日：2016-08-11

申请号：US14616999

申请日：2015-02-09

Applicant: United Technologies Corporation

Inventor： Christopher King ,  Edward F. Pietraszkiewicz

IPC: F01D5/18 ,  F01D9/06

CPC classification number: F01D5/187 ,  F01D5/08 ,  F01D5/18 ,  F01D5/186 ,  F01D5/188 ,  F01D9/065 ,  F05D2230/30 ,  F05D2260/2212 ,  F05D2260/2214 ,  F05D2260/22141 ,  Y02T50/676

Abstract: A. structure for creating a core for a gas turbine engine component comprises a body with a curved surface defining a turn passage. A plurality of protrusions are formed within a wall surface of the turn passage. A plurality of protrusions are configured to extend transversely relative to the curved surface. A gas turbine engine component is also disclosed.

Abstract translation: A.用于产生燃气涡轮发动机部件的核心的结构包括具有限定转向通道的弯曲表面的主体。 在转向通道的壁面内形成有多个突起。 多个突起构造成相对于弯曲表面横向延伸。 还公开了一种燃气轮机发动机部件。