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公开(公告)号：US10329916B2
公开(公告)日：2019-06-25
申请号：US14630814
申请日：2015-02-25
Applicant: UNITED TECHNOLOGIES CORPORATION
Abstract: A component for a gas turbine engine includes a trailing edge tip corner that at least partially defines a trailing edge cavity and a multiple of corner features within the trailing edge cavity, the multiple of corner features splayed along the trailing edge tip corner.
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公开(公告)号：US10301967B2
公开(公告)日：2019-05-28
申请号：US15028468
申请日：2014-10-17
Applicant: United Technologies Corporation
Inventor： Thomas N. Slavens , Steven Bruce Gautschi
IPC: F01D5/20 , F01D25/12 , F01D17/16 , F01D5/02 , F01D5/12 , F01D9/04 , F01D17/14 , F02C3/04 , F01D11/04 , F16J15/00 , F01D11/00
Abstract: A turbine vane assembly for a gas turbine engine is disclosed and includes an airfoil rotatable about a first axis transverse to an engine longitudinal axis. The airfoil includes an endwall and at least one protrusion disposed on the endwall configured for obstructing flow through a gap between the endwall and a static structure of the gas turbine engine.
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公开(公告)号：US10301947B2
公开(公告)日：2019-05-28
申请号：US15997943
申请日：2018-06-05
Applicant: United Technologies Corporation
Inventor： Tracy A. Propheter-Hinckley , Steven Bruce Gautschi , San Quach
Abstract: A method of manufacturing a component for a gas turbine engine according to an exemplary aspect of the present disclosure includes forming the component with a first manufacturing technique to include a first cavity and a second cavity, and a microcircuit in fluid communication with the first cavity, the component including an outer wall and a ribbed portion or a bulged portion extending from the outer wall. The exemplary method includes forming a plunged hole with a second manufacturing technique different from the first manufacturing technique to intersect at least a portion of the microcircuit and extend into the ribbed portion or the bulged portion.
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公开(公告)号：US20190078786A1
公开(公告)日：2019-03-14
申请号：US15699163
申请日：2017-09-08
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Tracy A. Propheter-Hinckley , Atul Kohli , Brandon W. Spangler , David J. Hyland , Dustin W. Davis , Ricardo Trindade , Stephen K. Kramer , Steven Bruce Gautschi
Abstract: A combustor panel may include an attachment feature. Because conventional attachment features of conventional combustor panels may be insufficiently cooled, the present disclosure provides various combustor configurations for reducing hotspots in the vicinity of attachment features and/or for providing cooling airflow to and in the vicinity of attachment features.
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公开(公告)号：US20190078785A1
公开(公告)日：2019-03-14
申请号：US15698967
申请日：2017-09-08
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Tracy A. Propheter-Hinckley , Atul Kohli , Benjamin D. Bellows , Brandon W. Spangler , David J. Hyland , Dennis M. Moura , Dustin W. Davis , Mark F. Zelesky , Ricardo Trindade , Stephen K. Kramer , Steven Bruce Gautschi , Trevor Rudy
CPC classification number: F23R3/60 , F23R3/002 , F23R3/06 , F23R3/54 , F23R2900/03041 , F23R2900/03042 , F23R2900/03043 , F23R2900/03044
Abstract: A combustor panel may include an attachment feature. Because conventional attachment features of conventional combustor panels may be insufficiently cooled, the present disclosure provides various combustor configurations for reducing hotspots in the vicinity of attachment features and/or for providing cooling airflow to and in the vicinity of attachment features.
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Patent Agency Ranking
公开(公告)号：US10125614B2
公开(公告)日：2018-11-13
申请号：US14689168
申请日：2015-04-17
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Dominic J. Mongillo , San Quach , Steven Bruce Gautschi , Brandon S. Donnell , Anita L. Tracy , Yafet Girma
IPC: F01D5/18
Abstract: A component for a gas turbine engine according to an exemplary aspect of this disclosure includes a surface having a plurality of cooling holes. The surface includes a first region and a second region each having a plurality of cooling holes. The cooling holes within the first region are arranged differently than the cooling holes in the second region.
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公开(公告)号：US10030523B2
公开(公告)日：2018-07-24
申请号：US14622000
申请日：2015-02-13
Applicant: United Technologies Corporation
Inventor： San Quach , Tracy A. Propheter-Hinckley , Steven Bruce Gautschi
Abstract: An article for gas turbine engine includes a body that has a gaspath side for exposure in a core gaspath of a gas turbine engine. The gaspath side has an undulating surface. A cooling passage is in the body. The cooling passage has a undulating profile that corresponds to the undulating surface.
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公开(公告)号：US10005123B2
公开(公告)日：2018-06-26
申请号：US15022745
申请日：2014-09-26
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Lane Thornton , San Quach , Steven Bruce Gautschi
Abstract: In a featured embodiment, a lost core assembly includes a ceramic component having a tapered shape in a radial direction. A refractory metal component extends radially from the ceramic core component. A method of molding a gas turbine engine component is also disclosed.
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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.
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公开(公告)号：US20160356161A1
公开(公告)日：2016-12-08
申请号：US14622000
申请日：2015-02-13
Applicant: United Technologies Corporation
Inventor： San Quach , Tracy A. Propheter-Hinckley , Steven Bruce Gautschi
CPC classification number: F01D5/18 , F01D5/143 , F01D5/187 , F01D11/006 , F01D25/12 , F02C7/18 , F05D2240/81 , F05D2250/184 , Y02T50/673 , Y02T50/676
Abstract: An article for gas turbine engine includes a body that has a gaspath side for exposure in a core gaspath of a gas turbine engine. The gaspath side has an undulating surface. A cooling passage is in the body. The cooling passage has a undulating profile that corresponds to the undulating surface.
Abstract translation: 燃气涡轮发动机的制品包括具有用于在燃气涡轮发动机的核心气体路径中曝光的气路侧的主体。 气路侧具有起伏的表面。 冷却通道在体内。 冷却通道具有对应于起伏表面的波形轮廓。
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