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公开(公告)号：US20160258322A1
公开(公告)日：2016-09-08
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.
Abstract translation: 根据本公开的示例的用于燃气涡轮发动机的中涡轮机框架包括第一框架壳体，联接到第一框架壳体的凸缘和邻近凸缘的相邻轮辐之间的隔热板 。 还公开了一种冷却燃气涡轮发动机的一部分的方法。
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公开(公告)号：US20160230602A1
公开(公告)日：2016-08-11
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
CPC classification number: F01D25/28 , F01D9/065 , F01D25/162 , F01D25/26 , F02C7/12 , F05D2220/32 , F05D2220/3213 , F05D2230/20 , F05D2230/64 , F05D2260/20 , F05D2260/30 , F05D2260/31 , Y02T50/671 , Y02T50/676
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.
Abstract translation: 用于中涡轮机架的拉杆组件包括用于将外框壳体连接到内框架壳体的至少一个拉杆。 至少一个拉杆包括分支到第一分支和第二分支中的入口通道。 插头位于第一分支中以阻止流过第一分支的一部分。
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公开(公告)号：US20160215639A1
公开(公告)日：2016-07-28
申请号：US14603126
申请日：2015-01-22
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Steven D. Porter , Jonathan Lemoine , Kevin Zacchera
CPC classification number: F01D11/005 , F01D25/125 , F01D25/162 , F02C3/10 , Y02T50/675
Abstract: According to one embodiment of the present invention, a sealing arrangement includes a turbine static structure with an inner case and a seal ring each having contact surfaces. The sealing arrangement also has a bearing compartment with a contact surface. A piston seal is positioned between the inner case, the seal ring, and the bearing compartment and is configured to contact the contact surfaces.
Abstract translation: 根据本发明的一个实施例，密封装置包括具有内壳和每个都具有接触表面的密封环的涡轮机静态结构。 密封装置还具有带有接触表面的轴承室。 活塞密封件位于内壳体，密封环和轴承室之间，并且构造成与接触表面接触。
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公开(公告)号：US11118480B2
公开(公告)日：2021-09-14
申请号：US15830558
申请日：2017-12-04
Applicant: United Technologies Corporation
Inventor： Jeffrey J. Lienau , Dustin W. Davis , Jonathan Lemoine , Kevin Zacchera
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.
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公开(公告)号：US20200277867A1
公开(公告)日：2020-09-03
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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Patent Agency Ranking
公开(公告)号：US10215098B2
公开(公告)日：2019-02-26
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
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.
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公开(公告)号：US20180298823A1
公开(公告)日：2018-10-18
申请号：US16011737
申请日：2018-06-19
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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公开(公告)号：US20180292089A1
公开(公告)日：2018-10-11
申请号：US15479981
申请日：2017-04-05
Applicant: United Technologies Corporation
Inventor： Steven D. Porter , Jonathan Lemoine , Kevin Zacchera
Abstract: A combustor panel of a combustor may include a combustion facing surface and a cooling surface opposite the combustion facing surface. An attachment feature may extend from the cooling surface. The attachment feature may define a first channel extending through the attachment feature to the combustion facing surface. The combustor channel may be formed by additive manufacturing.
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公开(公告)号：US20180128485A1
公开(公告)日：2018-05-10
申请号：US15343988
申请日：2016-11-04
Applicant: United Technologies Corporation
Inventor： Jonathan Jeffery Eastwood , Monica Pacheco-Tougas , Kevin Zacchera
IPC: F23R3/00
CPC classification number: F23R3/002 , F23R2900/00017 , F23R2900/03042
Abstract: A liner panel for use in a combustor of a gas turbine engine, the liner panel includes a stud free zone downstream of a combustor swirler. A combustor for a gas turbine engine, the combustor including a liner panel mounted to the support shell via a multiple of studs, the liner panel including a stud free zone downstream of each respective combustor swirler, the stud free zone including a multiple of film cooling holes. A method of directing airflow through a wall assembly within a combustor of a gas turbine engine including providing a stud free zone in a forward liner panel downstream of a combustor swirler, the stud free zone including a multiple of film cooling holes.
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公开(公告)号：US20180087406A1
公开(公告)日：2018-03-29
申请号：US15830558
申请日：2017-12-04
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.
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