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公开(公告)号：US10738701B2
公开(公告)日：2020-08-11
申请号：US15690555
申请日：2017-08-30
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 plurality of openings communicating cooling airflow into a gap between an aft end of the combustor and the first vane stage. A combustor assembly and method are also disclosed.
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公开(公告)号：US09869204B2
公开(公告)日：2018-01-16
申请号：US14640323
申请日：2015-03-06
Applicant: United Technologies Corporation
Inventor： Joshua Daniel Winn , Anthony P. Cherolis , Steven D. Porter , Christopher Treat , Kevin Zacchera
CPC classification number: F01D25/145 , F01D9/065 , F01D25/12 , F01D25/162 , F01D25/24 , F01D25/243 , F01D25/28 , F05D2260/20 , Y02T50/672 , Y02T50/676
Abstract: A mid-turbine frame for a gas turbine engine according to an example of the present disclosure includes, among other things, a first frame case, a flange coupled to the first frame case, and a heat shield adjacent to the flange and between adjacent spokes. A method of cooling a portion of a gas turbine engine is also disclosed.
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公开(公告)号：US20160230666A1
公开(公告)日：2016-08-11
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
CPC classification number: F02C7/20 , F01D5/081 , F02C7/12 , F05D2230/64 , F05D2260/14 , F05D2260/30 , F05D2260/36 , Y02T50/676
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.
Abstract translation: 用于燃气涡轮发动机的冷却结构包括限定冷却腔的燃气涡轮发动机结构。 冷却部件构造成将冷却流沿所需方向引导到冷却腔中。 支架支撑冷却部件并且具有附接接口以将支架固定到燃气涡轮发动机结构。 与支架相关联的第一个定向功能。 第二定向特征与燃气涡轮发动机结构相关联。 第一和第二取向特征彼此配合以确保冷却部件仅相对于燃气涡轮发动机结构安装在一个方位上。 还公开了一种燃气涡轮发动机和安装冷却结构的方法。
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公开(公告)号：US10577971B2
公开(公告)日：2020-03-03
申请号：US15806370
申请日：2017-11-08
Applicant: United Technologies Corporation
Inventor： Joshua Daniel Winn , Anthony P. Cherolis , Steven D. Porter , Christopher Treat , Kevin Zacchera
Abstract: A mid-turbine frame for a gas turbine engine according to an example of the present disclosure includes, among other things, a first frame case, a flange coupled to the first frame case, and a heat shield adjacent to the flange. A method of cooling a portion of a gas turbine engine is also disclosed.
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公开(公告)号：US20190063323A1
公开(公告)日：2019-02-28
申请号：US15690555
申请日：2017-08-30
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 plurality of openings communicating cooling airflow into a gap between an aft end of the combustor and the first vane stage. A combustor assembly and method are also disclosed.
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Patent Agency Ranking
公开(公告)号：US20180087402A1
公开(公告)日：2018-03-29
申请号：US15806370
申请日：2017-11-08
Applicant: United Technologies Corporation
Inventor： Joshua Daniel Winn , Anthony P. Cherolis , Steven D. Porter , Christopher Treat , Kevin Zacchera
CPC classification number: F01D25/145 , F01D9/065 , F01D25/12 , F01D25/162 , F01D25/24 , F01D25/243 , F01D25/28 , F05D2260/20 , Y02T50/672 , Y02T50/676
Abstract: A mid-turbine frame for a gas turbine engine according to an example of the present disclosure includes, among other things, a first frame case, a flange coupled to the first frame case, and a heat shield adjacent to the flange. A method of cooling a portion of a gas turbine engine is also disclosed.
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公开(公告)号：US20160312659A1
公开(公告)日：2016-10-27
申请号：US14695323
申请日：2015-04-24
Applicant: United Technologies Corporation
Inventor： Jeffrey J. Lienau , Dustin W. Davis , Jonathan Lemoine , Kevin Zacchera
CPC classification number: F01D25/28 , F01D9/042 , F01D9/065 , F01D11/003 , F01D25/12 , F01D25/162 , F05D2220/3213 , F05D2240/58 , F05D2260/20 , Y02T50/675
Abstract: A mid-turbine frame for a gas turbine engine includes an inner frame case defining a sealed torque box cavity. Multiple spokes protrude radially outward from the inner frame case, and at least one service line is connected to the inner frame case.
Abstract translation: 用于燃气涡轮发动机的中涡轮机框架包括限定密封的扭矩箱腔的内框架壳体。 多个轮辐从内框架径向向外突出，并且至少一个维修线连接到内框架。
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公开(公告)号：US10670269B2
公开(公告)日：2020-06-02
申请号：US15334860
申请日：2016-10-26
Applicant: United Technologies Corporation
Inventor： Jonathan Jeffery Eastwood , Kevin Zacchera , Brian T. Hazel , William F. Werkheiser
Abstract: A liner panel for use in a combustor of a gas turbine engine, the liner panel includes a radiused gate blended into a hot side of the liner 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 gate blended into a hot side of the liner panel, the hot side including a thermal barrier coating. A method of manufacturing including casting a radiused gate tangentially cast into a hot side of a liner panel; and applying a thermal barrier coating to the hot side of the liner panel over the remnant of the radiused gate.
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公开(公告)号：US10584601B2
公开(公告)日：2020-03-10
申请号：US15690615
申请日：2017-08-30
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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公开(公告)号：US20190063239A1
公开(公告)日：2019-02-28
申请号：US15690615
申请日：2017-08-30
Applicant: United Technologies Corporation
Inventor： Steven D. Porter , Shawn M. McMahon , Kevin Zacchera , Noah Wadsworth , Christopher Whitfield , Sean D. Bradshaw , Dennis M. Moura
CPC classification number: F01D9/023 , F01D9/041 , F01D11/005 , F01D25/12 , F05D2220/32 , F05D2240/11 , F05D2240/121 , F05D2240/55 , F05D2260/20
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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