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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：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：US20170362960A1
公开(公告)日：2017-12-21
申请号：US15188170
申请日：2016-06-21
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Christopher Treat , Jeffrey H. Huang , Caroline Karanian
CPC classification number: F01D25/24 , F01D9/041 , F01D25/28 , F05D2220/32 , F05D2230/10 , F05D2230/21 , F05D2230/237 , F05D2230/30
Abstract: A stiffness boss for a turbine case of a gas turbine engine is disclosed. The stiffness boss includes a head portion disposed on an outer case surface of the turbine case, the head portion configured to provide rigidity in response to a transverse load being applied to the turbine case in a transverse direction. The stiffness boss also includes a leg portion disposed on the outer case surface of the turbine case and connected to the head portion, the leg portion configured to provide rigidity in response to an axial load being applied to the turbine case in an axial direction, such that deformation of the turbine case is resisted.
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公开(公告)号：US20170241281A1
公开(公告)日：2017-08-24
申请号：US15052457
申请日：2016-02-24
Applicant: United Technologies Corporation
CPC classification number: F01D11/003 , F01D11/005 , F01D25/246 , F02C7/28 , F05D2220/32 , F05D2230/60 , F05D2240/58 , F05D2260/30 , F05D2260/36 , F16J9/24 , F16J15/3272 , Y02T50/671
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：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：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：US20190316491A1
公开(公告)日：2019-10-17
申请号：US16426707
申请日：2019-05-30
Applicant: United Technologies Corporation
Inventor： Joshua Daniel Winn , Alexander Broulidakis , Paul K. Sanchez , Anthony P. Cherolis , Joseph J. Sedor , Christopher Treat
Abstract: A method of cooling a portion of a gas turbine engine includes positioning a tie rod relative to an inner frame case. The tie rod includes a bushing opening and the inner frame case includes a fastener opening. A fastener is secured through the fastener opening in the inner frame case to a threaded bushing located in the bushing opening. The threaded bushing includes a distal end that forms a clearance gap with the inner frame case. Heat is transferred from the fastener through the threaded bushing to prevent the fastener from creeping.
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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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