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公开(公告)号：US10690346B2
公开(公告)日：2020-06-23
申请号：US15476431
申请日：2017-03-31
Applicant: United Technologies Corporation
Inventor： Tracy A. Propheter-Hinckley , Mark F. Zelesky , Atul Kohli , Dustin W. Davis , Ricardo Trindade , Steven Bruce Gautschi , Brandon W. Spangler , Trevor Rudy , Benjamin Bellows , Dave J. Hyland , James B. Hoke , Stephen K. Kramer , Dennis M. Moura
Abstract: A combustor for a gas turbine engine includes a combustor shell having a shell opening therethrough, a combustor panel having a stud attached thereto, the stud extending through the shell opening. The stud includes a standoff to define an intermediate passage between the combustor shell and the combustor panel. A retainer is attached to the stud. A washer surrounds the stud and is positioned between the retainer and the combustor shell. The washer at least partially defines a cooling flow passage configured to direct a cooling airflow through the shell opening to impinge the cooling flow on at least one of the stud or the standoff.
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公开(公告)号：US10670274B2
公开(公告)日：2020-06-02
申请号：US15699514
申请日：2017-09-08
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Benjamin D Bellows , Brandon W Spangler , David J Hyland , James B Hoke , Ricardo Trindade , 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：US20190218932A1
公开(公告)日：2019-07-18
申请号：US15874070
申请日：2018-01-18
Applicant: United Technologies Corporation
Inventor： Dominic J. Mongillo, JR. , Ricardo Trindade , Nicholas M. LoRicco
CPC classification number: F01D25/12 , F01D5/18 , F01D5/188 , F01D9/041 , F05D2220/32 , F05D2240/126 , F05D2260/202
Abstract: Divided baffles for a gas turbine engines are provided. The divided baffles include a baffle body having a first end and a second end, at least one divider located within the baffle body and extending from the first end to the second end arranged to divide an interior of the baffle body into two or more feed cavities, at least one cap arranged at the first end to bound a first feed cavity of the two or more feed cavities, and at least one cap arranged at the second end to bound a second feed cavity of the two or more feed cavities.
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公开(公告)号：US20180283181A1
公开(公告)日：2018-10-04
申请号：US15471731
申请日：2017-03-28
Applicant: United Technologies Corporation
Inventor： Carey Clum , Ricardo Trindade
Abstract: An airfoil has a pressure side wall and a suction side wall circumferentially spaced apart from the pressure side wall. Each radially extends between a root region and a tip region, and each axially extends between a leading edge and a trailing edge. The airfoil also has a gusset, a squealer pocket, and a tip pocket. The gusset extends between the pressure side wall and the suction side wall. The squealer pocket is formed in the tip region and is disposed between the leading edge, the gusset, the pressure side wall, and the suction side wall. The tip pocket is formed in the tip region and is spaced apart from the squealer pocket. The tip pocket is disposed between the trailing edge, the gusset, the pressure side wall, and the suction side wall.
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公开(公告)号：US11939883B2
公开(公告)日：2024-03-26
申请号：US16532603
申请日：2019-08-06
Applicant: United Technologies Corporation
Inventor： Allan N. Arisi , Ricardo Trindade , Dominic J. Mongillo , Tracy A. Propheter-Hinckley
IPC: F01D5/18
CPC classification number: F01D5/188 , F05D2260/22141
Abstract: An airfoil includes an airfoil section that has an airfoil wall that defines a leading end, an arced trailing end, and first and second sides that join the leading end and the arced trailing end. The first and second sides span in a longitudinal direction between first and second ends. The airfoil wall circumscribes an internal core cavity that includes an exit region that spans between the first and second ends and that opens through the arced trailing end. The exit region includes pedestals arranged in a plurality of longitudinal pedestal rows. At least one of the longitudinal pedestal rows is straight and at least one of the longitudinal pedestal rows is arced.
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Patent Agency Ranking
公开(公告)号：US10704396B2
公开(公告)日：2020-07-07
申请号：US15876579
申请日：2018-01-22
Applicant: United Technologies Corporation
Inventor： Nicholas M. LoRicco , Ricardo Trindade , Dominic J. Mongillo, Jr.
Abstract: Components for gas turbine engines are provided. The components include a hot external wall that is exposed to hot gaspath air when installed within a gas turbine engine, and an interior impingement wall, wherein the interior impingement wall defines a feed cavity and at least one impingement cavity is defined between the impingement wall and the external wall. The impingement wall includes a plurality of impingement holes that fluidly connect the feed cavity to the at least one impingement cavity, the external wall includes a plurality of film holes that fluidly connect the at least one impingement cavity to an exterior surface of the external wall, and wherein the only source of cooling air within the at least one impingement cavity is the feed cavity.
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公开(公告)号：US10697307B2
公开(公告)日：2020-06-30
申请号：US15875500
申请日：2018-01-19
Applicant: United Technologies Corporation
Inventor： Nicholas M. LoRicco , Ricardo Trindade , Dominic J. Mongillo, Jr.
Abstract: Airfoils for gas turbine engines are provided. The airfoils include an airfoil body extending between a first platform and a second platform, a first platform feed cavity defined by the first platform, a second platform exit cavity defined by the second platform, a first hybrid skin core cooling cavity passage formed within the airfoil body and fluidly connecting the first platform feed cavity to the second platform exit cavity, and at least one purge aperture formed in the second platform and fluidly connecting the second platform exit cavity to an exterior of the second platform. The airfoil body does not include any apertures fluidly connecting the first hybrid skin core cooling cavity passage to an exterior of the airfoil body.
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公开(公告)号：US10670273B2
公开(公告)日：2020-06-02
申请号：US15698967
申请日：2017-09-08
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Tracy A Propheter-Hinckley , Benjamin D Bellows , Brandon W Spangler , David J Hyland , Dennis M Moura , Dustin W Davis , Mark F Zelesky , Ricardo Trindade , Steven Bruce Gautschi , Trevor Rudy
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：US20190226344A1
公开(公告)日：2019-07-25
申请号：US15875500
申请日：2018-01-19
Applicant: United Technologies Corporation
Inventor： Nicholas M. LoRicco , Ricardo Trindade , Dominic J. Mongillo, JR.
Abstract: Airfoils for gas turbine engines are provided. The airfoils include an airfoil body extending between a first platform and a second platform, a first platform feed cavity defined by the first platform, a second platform exit cavity defined by the second platform, a first hybrid skin core cooling cavity passage formed within the airfoil body and fluidly connecting the first platform feed cavity to the second platform exit cavity, and at least one purge aperture formed in the second platform and fluidly connecting the second platform exit cavity to an exterior of the second platform. The airfoil body does not include any apertures fluidly connecting the first hybrid skin core cooling cavity passage to an exterior of the airfoil body.
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公开(公告)号：US11434770B2
公开(公告)日：2022-09-06
申请号：US15471731
申请日：2017-03-28
Applicant: United Technologies Corporation
Inventor： Carey Clum , Ricardo Trindade
Abstract: An airfoil has a pressure side wall and a suction side wall circumferentially spaced apart from the pressure side wall. Each radially extends between a root region and a tip region, and each axially extends between a leading edge and a trailing edge. The airfoil also has a gusset, a squealer pocket, and a tip pocket. The gusset extends between the pressure side wall and the suction side wall. The squealer pocket is formed in the tip region and is disposed between the leading edge, the gusset, the pressure side wall, and the suction side wall. The tip pocket is formed in the tip region and is spaced apart from the squealer pocket. The tip pocket is disposed between the trailing edge, the gusset, the pressure side wall, and the suction side wall.
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