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公开(公告)号：US09810091B2
公开(公告)日：2017-11-07
申请号：US14823568
申请日：2015-08-11
Applicant: United Technologies Corporation
Inventor： Kevin Zacchera , Patrick D. Couture
CPC classification number: F01D21/003 , F01D5/225 , F01D11/20 , F05D2220/30 , F05D2240/11 , F05D2260/81 , F05D2260/83 , F05D2270/20 , F05D2270/44 , F05D2270/71
Abstract: A method is provided for calibrating an active clearance control system for a plurality of turbine engines. During this method, a squeeze test is performed between a tip of a rotor blade and a shroud. Results of the squeeze test are applied to adjust a gap between the tip and the shroud. The performance of the squeeze test and the application of the results may be individually performed for each of the turbine engines.
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公开(公告)号：US20160215702A1
公开(公告)日：2016-07-28
申请号：US14603088
申请日：2015-01-22
Applicant: United Technologies Corporation
Inventor： Anthony P. Cherolis , Jorge I. Farah , Seth A. Max , John H. Mosley , Steven D. Porter , Gregory E. Reinhardt , Kevin Zacchera
CPC classification number: F02C7/28 , F01D11/005 , F01D25/125 , F01D25/162 , F02C3/14 , F02C7/06 , F05D2220/32 , F05D2230/60 , F05D2240/55 , F16J15/06 , Y02T50/675
Abstract: A sealing arrangement includes a turbine static structure with a seal ring having groove with a contact surface. Also included is a bearing compartment with a second contact surface, and a piston seal positioned between the turbine static structure and the bearing compartment. The piston seal includes sides configured to contact the contact surfaces and is positioned in the groove.
Abstract translation: 密封装置包括具有密封环的涡轮机静态结构，其具有带有接触表面的凹槽。 还包括具有第二接触表面的轴承室和位于涡轮机静态结构和轴承室之间的活塞密封件。 活塞密封件包括被配置为接触接触表面并定位在凹槽中的侧面。
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公开(公告)号：US11015464B2
公开(公告)日：2021-05-25
申请号：US16751298
申请日：2020-01-24
Applicant: United Technologies Corporation
Inventor： Steven D. Porter , Shawn M. McMahon , Kevin Zacchera , Noah Wadsworth , Christopher Whitfield , Sean D. Bradshaw , Dennis M. Moura
Abstract: A gas turbine engine includes a combustor. A turbine section is in fluid communication with the combustor. The turbine section includes a first vane stage aft of the combustor. A seal assembly is disposed between the combustor and the first vane stage. The seal assembly includes a first plurality of openings and the first vane stage includes a second plurality of openings communicating cooling airflow into a gap between an aft end of the combustor and the first vane stage. A first vane stage assembly and a method are also disclosed.
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24.发明授权公开(公告)号：US10830448B2
公开(公告)日：2020-11-10
申请号：US15334776
申请日：2016-10-26
Applicant: United Technologies Corporation
Inventor： Monica Pacheco-Tougas , Kevin Zacchera , Jonathan Jeffery Eastwood
Abstract: A liner panel for use in a combustor of a gas turbine engine, including a multiple of heat transfer augmentors located in at least one discrete area of the liner panel. A wall assembly within a gas turbine engine including a support shell, a liner panel mounted to the support shell via a multiple of studs and a multiple of heat transfer augmentors located in at least one discrete area on a cold side of the liner panel, each of the multiple of heat transfer augmentors define a height that extends about half the distance between a cold surface of the liner panel and the support shell.
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公开(公告)号：US10823410B2
公开(公告)日：2020-11-03
申请号：US15334879
申请日：2016-10-26
Applicant: United Technologies Corporation
Inventor： Jonathan Jeffery Eastwood , Kevin Zacchera , Brian T. Hazel , William F. Werkheiser
IPC: F23R3/00
Abstract: A liner panel for use in a combustor of a gas turbine engine, the liner panel includes a radiused edge blended into a hot side of the linear panel. A combustor for a gas turbine engine including a liner panel mounted to a support shell via a multiple of studs, the liner panel including a radiused edge blended into a hot side of the linear panel, the hot side including a thermal barrier coating. A method of manufacturing including casting a radiused edge blended into a hot side of a linear panel; and applying a thermal barrier coating to the hot side of the liner panel.
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Patent Agency Ranking
公开(公告)号：US20190107059A1
公开(公告)日：2019-04-11
申请号：US15729148
申请日：2017-10-10
Applicant: United Technologies Corporation
Inventor： Kevin Zacchera , Jonathan Lemoine
Abstract: A combustor cooling system for a combustor of a gas turbine engine is provided. The combustor cooling system comprising: a heat exchanger fluidly connected to a compressor section of the gas turbine engine, the heat exchanger being configured to receive compressor bleed air from the compressor section and cool the compressor bleed air; and a plenum assembly fluidly connected to the heat exchanger, the plenum assembly configured to receive cooled compressor bleed air from the heat exchanger and distribute the cooled compressor bleed air to one or more areas of the combustor.
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公开(公告)号：US10087785B2
公开(公告)日：2018-10-02
申请号：US14617323
申请日：2015-02-09
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Alexander Broulidakis , Anthony P. Cherolis , Jonathan Lemoine , Kalpendu J. Parekh , Steven W. Trinks , Christopher Treat , Kevin Zacchera , Alberto A. Mateo
Abstract: A tie rod assembly for a mid-turbine frame includes at least one tie rod for connecting an outer frame case to an inner frame case. At least one tie rod includes an inlet passage that branches into a first branch and a second branch. A plug is located in the first branch to block flow through a portion of the first branch.
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公开(公告)号：US10030582B2
公开(公告)日：2018-07-24
申请号：US14617109
申请日：2015-02-09
Applicant: United Technologies Corporation
Inventor： Kevin Zacchera , Matthew Andrew Hough , Jonathan Lemoine , Christopher Treat , Alberto A. Mateo
Abstract: A cooling structure for a gas turbine engine comprises a gas turbine engine structure defining a cooling cavity. A cooling component is configured to direct cooling flow in a desired direction into the cooling cavity. A bracket supports the cooling component and has an attachment interface to fix the bracket to the gas turbine engine structure. A first orientation feature associated with the bracket. A second orientation feature is associated with the gas turbine engine structure. The first and second orientation features cooperate with each other to ensure that the cooling component is only installed in one orientation relative to the gas turbine engine structure. A gas turbine engine and a method of installing a cooling structure are also disclosed.
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29.发明申请公开(公告)号：US20180112878A1
公开(公告)日：2018-04-26
申请号：US15334776
申请日：2016-10-26
Applicant: United Technologies Corporation
Inventor： Monica Pacheco-Tougas , Kevin Zacchera , Jonathan Jeffery Eastwood
Abstract: A liner panel for use in a combustor of a gas turbine engine, including a multiple of heat transfer augmentors located in at least one discrete area of the liner panel. A wall assembly within a gas turbine engine including a support shell, a liner panel mounted to the support shell via a multiple of studs and a multiple of heat transfer augmentors located in at least one discrete area on a cold side of the liner panel, each of the multiple of heat transfer augmentors define a height that extends about half the distance between a cold surface of the liner panel and the support shell.
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公开(公告)号：US20180112877A1
公开(公告)日：2018-04-26
申请号：US15334879
申请日：2016-10-26
Applicant: United Technologies Corporation
Inventor： Jonathan Jeffery Eastwood , Kevin Zacchera , Brian T. Hazel , William F. Werkheiser
IPC: F23R3/00
CPC classification number: F23R3/002 , F23R2900/00018 , F23R2900/03041 , F23R2900/03042 , Y02T50/675 , Y02T50/6765
Abstract: A liner panel for use in a combustor of a gas turbine engine, the liner panel includes a radiused edge blended into a hot side of the linear panel. A combustor for a gas turbine engine including a liner panel mounted to a support shell via a multiple of studs, the liner panel including a radiused edge blended into a hot side of the linear panel, the hot side including a thermal barrier coating. A method of manufacturing including casting a radiused edge blended into a hot side of a linear panel; and applying a thermal barrier coating to the hot side of the liner panel.
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