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公开(公告)号：US10422232B2
公开(公告)日：2019-09-24
申请号：US15601007
申请日：2017-05-22
Applicant: United Technologies Corporation
Inventor： Christopher King
Abstract: A component for a gas turbine engine includes a wall that has an exterior surface and an interior surface spaced from the exterior surface. A cooling circuit extends from the interior surface to the exterior surface. The cooling circuit includes a feed passage that has a first end defining an inlet at the interior surface and a second end spaced from the first end. At least one second passage is in fluid communication with the feed passage. At least one slot passage is in fluid communication with the second end of the feed passage and a cooling slot in the exterior surface.
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公开(公告)号：US10156144B2
公开(公告)日：2018-12-18
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
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.
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公开(公告)号：US20180328227A1
公开(公告)日：2018-11-15
申请号：US15592677
申请日：2017-05-11
Applicant: United Technologies Corporation
Inventor： Christopher King
CPC classification number: F01D25/28 , F01D25/243 , F01D25/30 , F02C7/20 , F02K1/822 , F05D2230/642 , F05D2260/30
Abstract: A hanger for mounting an exhaust liner to an exhaust duct is provided. The hanger includes at least one cable, a cable flange, and a J-shaped flange. The at least one cable extends lengthwise between a first end and a second end. The cable flange has at least one cable aperture configured to receive a portion of the cable. The J-shaped liner flange is configured for attachment to the exhaust liner. The liner flange and cable flange are configured to mate with one another to prevent substantial relative motion between the cable flange and the liner flange in a first direction and in a second direction. The first and second directions are substantially orthogonal to one another.
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公开(公告)号：US10053992B2
公开(公告)日：2018-08-21
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
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.
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公开(公告)号：US20160230565A1
公开(公告)日：2016-08-11
申请号：US14618912
申请日：2015-02-10
Applicant: United Technologies Corporation
Inventor： Christopher King , San Quach , Steven Bruce Gautschi
CPC classification number: F01D5/187 , B22C9/103 , F01D5/18 , F01D9/041 , F01D25/12 , F05D2220/32 , F05D2230/211 , F05D2260/201 , F05D2260/202 , Y02T50/676
Abstract: An airfoil according to an example of the present disclosure includes, among other things, an airfoil section having an external wall and an internal wall. The internal wall defines a reference plane extending in a spanwise direction along a surface of the internal wall, a first cavity and a second cavity separated by the internal wall, and a plurality of crossover passages within the internal wall and connecting the first cavity to the second cavity. Each of the plurality of crossover passages defines a passage axis. The passage axis of each of the plurality of crossover passages is arranged at a radial angle relative to a localized region of the reference plane such that the radial angle of at least some of the plurality of crossover passages differs in the spanwise direction.
Abstract translation: 根据本公开的示例的翼型件尤其包括具有外壁和内壁的翼型部分。 内壁限定沿着内壁的表面沿翼展方向延伸的参考平面，由内壁分隔的第一腔和第二腔，以及在内壁内的多个交叉通道，并将第一腔连接到 第二腔。 多个交叉通道中的每一个限定通道轴线。 多个交叉通道中的每一个的通道轴线相对于参考平面的局部区域以径向角度布置，使得多个交叉通道中的至少一些的径向角在翼展方向上不同。
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Patent Agency Ranking
公开(公告)号：US11143040B2
公开(公告)日：2021-10-12
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
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.
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公开(公告)号：US10794194B2
公开(公告)日：2020-10-06
申请号：US15972475
申请日：2018-05-07
Applicant: United Technologies Corporation
Inventor： Christopher King
IPC: F01D5/18 , B22C9/10 , B23K26/382 , B22D25/02 , B23H9/14 , F01D5/14 , F01D9/04 , F01D11/08 , F01D25/12 , F02C7/18 , F23R3/00
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.
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公开(公告)号：US10533457B2
公开(公告)日：2020-01-14
申请号：US15592677
申请日：2017-05-11
Applicant: United Technologies Corporation
Inventor： Christopher King
Abstract: A hanger for mounting an exhaust liner to an exhaust duct is provided. The hanger includes at least one cable, a cable flange, and a J-shaped flange. The at least one cable extends lengthwise between a first end and a second end. The cable flange has at least one cable aperture configured to receive a portion of the cable. The J-shaped liner flange is configured for attachment to the exhaust liner. The liner flange and cable flange are configured to mate with one another to prevent substantial relative motion between the cable flange and the liner flange in a first direction and in a second direction. The first and second directions are substantially orthogonal to one another.
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公开(公告)号：US20180334908A1
公开(公告)日：2018-11-22
申请号：US15601007
申请日：2017-05-22
Applicant: United Technologies Corporation
Inventor： Christopher King
CPC classification number: F01D5/186 , F01D5/187 , F01D9/041 , F01D11/08 , F04D29/324 , F04D29/542 , F04D29/582 , F05D2230/211 , F05D2260/202 , F05D2260/204 , F23R3/002
Abstract: A component for a gas turbine engine includes a wall that has an exterior surface and an interior surface spaced from the exterior surface. A cooling circuit extends from the interior surface to the exterior surface. The cooling circuit includes a feed passage that has a first end defining an inlet at the interior surface and a second end spaced from the first end. At least one second passage is in fluid communication with the feed passage. At least one slot passage is in fluid communication with the second end of the feed passage and a cooling slot in the exterior surface.
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公开(公告)号：US09988910B2
公开(公告)日：2018-06-05
申请号：US14609677
申请日：2015-01-30
Applicant: United Technologies Corporation
Inventor： Christopher King
IPC: F02C1/00 , F01D5/18 , B22C9/10 , B23K26/382 , B22D25/02 , B23H9/14 , F01D5/14 , F01D9/04 , F01D11/08 , F01D25/12 , F02C7/18 , F23R3/00
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.
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