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公开(公告)号：US20210062670A1
公开(公告)日：2021-03-04
申请号：US16552347
申请日：2019-08-27
Applicant: United Technologies Corporation
Inventor： Christina G. Ciamarra , Anthony B. Swift
IPC: F01D11/08
Abstract: A blade outer air seal for a gas turbine engine includes a platform having a leading edge and a trailing edge. A pair of circumferential edges connect the leading edge and the trailing edge. An end wall protrudes radially outward from the platform at the trailing edge. A first support rib connects one of the circumferential edges to the end wall and structurally supports the end wall. A first boss portion extends axially forward from the end wall and is disposed radially outward of the first support rib.
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公开(公告)号：US20160169016A1
公开(公告)日：2016-06-16
申请号：US14880403
申请日：2015-10-12
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Ken F. Blaney , Anthony B. Swift , Neil L. Tatman , Paul M. Lutjen , Christopher M. Jarochym
CPC classification number: F01D9/065 , B22C9/10 , F01D11/08 , F01D11/122 , F01D25/246 , F05D2230/211 , F05D2240/11 , F05D2260/204 , Y02T50/676
Abstract: A casting core for a Blade Outer Air Seal includes a heat exchange cavity core section in communication with a first plenum section and a second plenum section, the first plenum and the second plenum section are of a thickness greater than the heat exchange cavity section.
Abstract translation: 用于叶片外部空气密封件的铸造芯部包括与第一增压部分和第二增压部分连通的热交换腔芯部分，第一增压室和第二增压部分的厚度大于热交换腔部分。
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公开(公告)号：US20170089204A1
公开(公告)日：2017-03-30
申请号：US14870175
申请日：2015-09-30
Applicant: United Technologies Corporation
Inventor： Anthony B. Swift , Paul M. Lutjen
CPC classification number: F01D5/186 , F01D9/02 , F01D11/08 , F01D25/12 , F02C3/04 , F05D2220/32 , F05D2240/11 , F05D2260/202 , F23R3/002
Abstract: A gas turbine engine component includes a wall portion that includes a first side and a second opposite side. A plurality of passages extends between the first side of the wall portion and the second side of the wall portion and includes a plurality of inlets located on the first side of the wall portion. A plurality of outlets are located on a second side of the wall portion. The plurality of outlets include a first plurality of outlets located on a first side of the plurality of inlets and a second plurality of outlets located on a second side of the plurality of inlets.
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公开(公告)号：US20190226406A1
公开(公告)日：2019-07-25
申请号：US16375064
申请日：2019-04-04
Applicant: United Technologies Corporation
Inventor： Paul M. Lutjen , Anthony B. Swift
Abstract: An air-driven particle pulverizer for a gas turbine engine includes an array of fingers arranged about an axis. Each of the fingers comprises a base and a terminal end. Each terminal end extends away from the axis and canted toward one side. The terminal ends are configured to pulverize particles in a fluid directed onto the terminal ends.
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公开(公告)号：US10323573B2
公开(公告)日：2019-06-18
申请号：US14804926
申请日：2015-07-21
Applicant: United Technologies Corporation
Inventor： Paul M. Lutjen , Anthony B. Swift
Abstract: A cooling fluid system for a gas turbine engine includes a structure that provides a fluid passageway. The structure has a wall with an aperture that is in fluid communication with the fluid passageway. The aperture is configured to provide a fluid in a flow direction. Fingers are arranged in the fluid passageway facing into flow direction. The fluid passageway includes a cooling cavity immediately downstream from the fingers and it is configured to receive fluid having passed over or through the fingers.
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Patent Agency Ranking
公开(公告)号：US10815827B2
公开(公告)日：2020-10-27
申请号：US15005061
申请日：2016-01-25
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Anthony B. Swift , Ken F. Blaney , Paul M. Lutjen , Neil L. Tatman , Dominic J. Mongillo
Abstract: A gas turbine engine component has a body extending between two circumferential sides, and between a leading edge and a trailing edge. A refractory metal core within the body forms at least one cooling circuit to utilize fluid to cool the body. When the refractory metal core is removed from the body, the at least one cooling circuit includes an inlet, an outlet, and a passage that varies in cross-sectional area between the inlet and outlet. A method of manufacturing a gas turbine engine, a method of manufacturing a core, and a refractory metal core are also disclosed.
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公开(公告)号：US10352184B2
公开(公告)日：2019-07-16
申请号：US15339581
申请日：2016-10-31
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Jose R. Paulino , Ken F. Blaney , Terence P. Tyler, Jr. , Daniel S. Rogers , Anthony B. Swift , Thomas E. Clark
Abstract: A seal assembly includes a blade outer air seal, a downstream vane, and a pressure wall, according to various embodiments. The blade outer air seal may include a radially outer surface and the downstream vane may be coupled to the blade outer air seal via a fluid sealing engagement. The pressure wall may be coupled to the blade outer air seal and may define a metering orifice. In various embodiments, the metering orifice of the pressure wall is configured to meter air flow from a first plenum upstream of the pressure wall to a second plenum downstream of the pressure wall. In various embodiments, at least a preponderance of the radially outer surface of the blade outer air seal at least partially defines the first plenum and the fluid sealing engagement at least partially defines the second plenum.
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公开(公告)号：US10145308B2
公开(公告)日：2018-12-04
申请号：US14611920
申请日：2015-02-02
Applicant: United Technologies Corporation
Inventor： Carson A. Roy Thill , Mark Broomer , Timothy M. Davis , Craig R. McGarrah , Mark J. Rogers , Russell E. Keene , Anthony B. Swift
Abstract: A seal assembly for a gas turbine engine includes an engine static structure. First and second members fluidly separate cavities from one another. A seal assembly is captured by the engine structure. The seal assembly includes a carrier and a seal that engages the first member. The second member is captured by the carrier.
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公开(公告)号：US10100667B2
公开(公告)日：2018-10-16
申请号：US14997315
申请日：2016-01-15
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Anthony B. Swift , Paul M. Lutjen , Neil L. Tatman , Dominic J. Mongillo, Jr. , Matthew A. Devore , Ken F. Blaney
Abstract: A gas turbine engine component is provided. The gas turbine engine component comprises a main body and a leading edge cooling passage defined within the main body. The main body has a leading edge and a leading edge wall including an elongated transition portion extending between the leading edge and a proximate flowpath surface of the main body. The leading edge cooling passage comprises an axial flow cooling passage defined within the main body and adjacent to the leading edge wall and has a leading edge periphery that generally conforms to the elongated transition portion of the leading edge wall.
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10.发明申请AIR-DRIVEN PARTICLE PULVERIZER FOR GAS TURBINE ENGINE COOLING FLUID SYSTEM 审中-公开用于气体涡轮发动机冷却流体系统的空气驱动颗粒式搅拌机公开(公告)号：US20160032835A1
公开(公告)日：2016-02-04
申请号：US14804926
申请日：2015-07-21
Applicant: United Technologies Corporation
Inventor： Paul M. Lutjen , Anthony B. Swift
IPC: F02C7/05
CPC classification number: F02C7/18 , F01D11/12 , F05D2240/11 , F05D2260/607 , Y02T50/671 , Y02T50/675
Abstract: A cooling fluid system for a gas turbine engine includes a structure that provides a fluid passageway. The structure has a wall with an aperture that is in fluid communication with the fluid passageway. The aperture is configured to provide a fluid in a flow direction. Fingers are arranged in the fluid passageway facing into flow direction. The fluid passageway includes a cooling cavity immediately downstream from the fingers and it is configured to receive fluid having passed over or through the fingers.
Abstract translation: 用于燃气涡轮发动机的冷却流体系统包括提供流体通道的结构。 该结构具有带有与流体通道流体连通的孔的壁。 孔被配置成在流动方向上提供流体。 手指布置在面向流动方向的流体通道中。 流体通道包括紧邻手指下游的冷却腔，并且其构造成接收经过手指或通过手指的流体。
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