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公开(公告)号：US20150285157A1
公开(公告)日：2015-10-08
申请号：US14615665
申请日：2015-02-06
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Andrew D. Burdick , Thomas J. Praisner , Andrew S. Aggarwala , Eric A. Hudson , Michael G. McCaffrey
CPC classification number: F02C9/20 , F01D5/148 , F01D9/02 , F01D11/025 , F01D17/162 , F02C3/04 , F05D2240/122 , Y02T50/672 , Y02T50/673 , Y10T137/0536
Abstract: One exemplary embodiment of this disclosure relates to a system including an airfoil having a static portion, a moveable portion, and a seal between the static portion and the moveable portion. The seal is moveable separate from the static portion and the moveable portion.
Abstract translation: 本公开的一个示例性实施例涉及一种包括具有静态部分，可移动部分以及静态部分和可移动部分之间的密封件的翼型的系统。 密封件可与静态部分和可移动部分分开地移动。
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2.发明申请公开(公告)号：US20190041059A1
公开(公告)日：2019-02-07
申请号：US15665837
申请日：2017-08-01
Applicant: United Technologies Corporation
Inventor： Thomas N. Slavens , Mark F. Zelesky , Andrew D. Burdick
Abstract: A liner panel for use in a combustor of a gas turbine engine, including a multiple of heat transfer ribs 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 ribs located in at least one discrete area on a cold side of the liner panel, each of the multiple of heat transfer ribs account for the multiple of studs.
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公开(公告)号：US10458339B2
公开(公告)日：2019-10-29
申请号：US14993129
申请日：2016-01-12
Applicant: United Technologies Corporation
Inventor： Christopher Treat , Alexander Broulidakis , Andrew D. Burdick
Abstract: A gas turbine engine component has an engine case structure surrounding an engine center axis. A plurality of holes are formed in the engine case structure, wherein the holes are circumferentially spaced apart from each other about the engine center axis. The plurality of holes includes at least one balance hole and at least one service hole that is configured to allow another engine component to pass through the at least one service hole. At least one cover is configured to cover at least one balance hole such that air is prevented from passing through the at least one balance hole.
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公开(公告)号：US20190145271A1
公开(公告)日：2019-05-16
申请号：US16245691
申请日：2019-01-11
Applicant: United Technologies Corporation
IPC: F01D11/00 , F16J9/24 , F02C7/28 , F01D25/24 , F16J15/3272
Abstract: A method of limiting circumferential rotation of a split-ring seal for use in a gas turbine engine includes inserting a retention block through a slot in a flange of a support structure and into a groove configured to hold a split-ring seal, and engaging an end of a split-ring seal in the groove with a surface of the retention block.
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公开(公告)号：US10215043B2
公开(公告)日：2019-02-26
申请号：US15052457
申请日：2016-02-24
Applicant: United Technologies Corporation
IPC: F01D11/00 , F02C7/28 , F16J9/24 , F01D25/24 , F16J15/3272
Abstract: A method of limiting circumferential rotation of a split-ring seal for use in a gas turbine engine includes inserting a retention block through a slot in a flange of a support structure and into a groove configured to hold a split-ring seal, and engaging an end of a split-ring seal in the groove with a surface of the retention block.
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Patent Agency Ranking
公开(公告)号：US09995171B2
公开(公告)日：2018-06-12
申请号：US14598452
申请日：2015-01-16
Applicant: United Technologies Corporation
Inventor： Andrew D. Burdick , Anthony P. Cherolis , Christopher Treat , Jonathan Lemoine , Robert Russell Mayer , Jorge I. Farah , John H. Mosley
CPC classification number: F01D25/12 , F01D5/02 , F01D5/081 , F01D9/065 , F01D25/125 , F01D25/162 , F01D25/26 , F02C7/12 , F05D2220/32 , F05D2260/2212 , Y02T50/673 , Y02T50/676
Abstract: A mid-turbine frame for a gas turbine engine includes an outer frame case and an inner frame case. At least one spoke connects the outer frame case to the inner frame case. The spoke includes an inlet passage with at least one branch that extends in an axial direction.
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公开(公告)号：US20160024938A1
公开(公告)日：2016-01-28
申请号：US14804865
申请日：2015-07-21
Applicant: United Technologies Corporation
Inventor： Thomas N. Slavens , Brooks E. Snyder , Andrew D. Burdick
IPC: F01D5/18
CPC classification number: F01D5/187 , F05D2220/32 , F05D2240/303 , F05D2250/322 , F05D2260/2212 , Y02T50/676
Abstract: An airfoil for a gas turbine engine, the airfoil includes a wall that has a leading edge and a trailing edge and at least partially defining a boundary of a leading edge cavity radially along the leading edge. A cooling jet structure is operatively associated with a portion of the wall proximate the leading edge and is configured to direct a cooling fluid tangent to the portion of the wall.
Abstract translation: 用于燃气涡轮发动机的翼型件，翼型件包括具有前缘和后缘的壁，并且沿着前缘至少部分地限定前缘腔的边界径向地限定。 冷却射流结构与靠近前缘的壁的一部分可操作地相关联，并且构造成引导与壁的该部分相切的冷却流体。
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8.发明授权公开(公告)号：US10247419B2
公开(公告)日：2019-04-02
申请号：US15665837
申请日：2017-08-01
Applicant: United Technologies Corporation
Inventor： Thomas N. Slavens , Mark F. Zelesky , Andrew D. Burdick
Abstract: A liner panel for use in a combustor of a gas turbine engine, including a multiple of heat transfer ribs 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 ribs located in at least one discrete area on a cold side of the liner panel, each of the multiple of heat transfer ribs account for the multiple of studs.
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公开(公告)号：US20170198642A1
公开(公告)日：2017-07-13
申请号：US14993129
申请日：2016-01-12
Applicant: United Technologies Corporation
Inventor： Christopher Treat , Alexander Broulidakis , Andrew D. Burdick
CPC classification number: F02C7/32 , F01D9/065 , F01D25/14 , F01D25/24 , F01D25/243 , F02C3/04 , F02C7/20 , F05D2300/501
Abstract: A gas turbine engine component has an engine case structure surrounding an engine center axis. A plurality of holes are formed in the engine case structure, wherein the holes are circumferentially spaced apart from each other about the engine center axis. The plurality of holes includes at least one balance hole and at least one service hole that is configured to allow another engine component to pass through the at least one service hole. At least one cover is configured to cover at least one balance hole such that air is prevented from passing through the at least one balance hole.
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公开(公告)号：US20160208644A1
公开(公告)日：2016-07-21
申请号：US14598452
申请日：2015-01-16
Applicant: United Technologies Corporation
Inventor： Andrew D. Burdick , Anthony P. Cherolis , Christopher Treat , Jonathan Lemoine , Robert Russell Mayer , Jorge I. Farah , John H. Mosley
CPC classification number: F01D25/12 , F01D5/02 , F01D5/081 , F01D9/065 , F01D25/125 , F01D25/162 , F01D25/26 , F02C7/12 , F05D2220/32 , F05D2260/2212 , Y02T50/673 , Y02T50/676
Abstract: A mid-turbine frame for a gas turbine engine includes an outer frame case and an inner frame case. At least one spoke connects the outer frame case to the inner frame case. The spoke includes an inlet passage with at least one branch that extends in an axial direction.
Abstract translation: 用于燃气涡轮发动机的中涡轮机架包括外框壳体和内框架壳体。 至少一个辐条将外框架连接到内框架。 辐条包括具有沿轴向方向延伸的至少一个分支的入口通道。
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