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公开(公告)号：US10428659B2
公开(公告)日：2019-10-01
申请号：US14976041
申请日：2015-12-21
Applicant: United Technologies Corporation
Inventor： Benjamin F. Hagan , Matthew A. Devore , Dominic J. Mongillo , Ryan Alan Waite
Abstract: A flowpath component for a gas turbine engine includes a leading edge, a trailing edge connected to the leading edge via a first surface and a second surface, an impingement cavity internal to the flowpath component, the impingement cavity being aligned with one of the leading edge and the trailing edge, a cooling passage extending at least partially through the flowpath component, and a plurality of crossover holes connecting the cooling passage to the impingement cavity. At least one of the crossover holes is aligned normal to an expected direction of fluid flow through the cooling passage and is unaligned with an axial line drawn perpendicular to a stacking line of the flowpath component.
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公开(公告)号：US20190048736A1
公开(公告)日：2019-02-14
申请号：US16164958
申请日：2018-10-19
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Michael G. McCaffrey , Benjamin F. Hagan , David Richard Griffin
CPC classification number: F01D11/12 , F01D5/02 , F01D9/041 , F01D11/08 , F01D25/08 , F02C7/28 , F05D2220/32 , F05D2230/60 , F05D2240/11 , F05D2260/231 , F05D2260/30 , F05D2260/38 , F05D2260/52 , Y02T50/672
Abstract: A seal assembly includes a seal arc segment defining first and second seal supports with a carriage defining first and second support members. The first support member supports the seal arc segment in a first ramped interface, and the second support member supports the seal arc segment in a second ramped interface. A spring is configured to bias the seal arc segment axially. A heat shield is radially inward of the spring.
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公开(公告)号：US10018062B2
公开(公告)日：2018-07-10
申请号：US14790589
申请日：2015-07-02
Applicant: United Technologies Corporation
Inventor： Ryan Alan Waite , Jeffrey Michael Jacques , Benjamin F. Hagan
CPC classification number: F01D9/065 , F01D9/02 , F01D9/06 , F01D25/12 , F05D2220/32 , F05D2240/12 , F05D2260/20 , F16L9/006 , Y02T50/675
Abstract: What is described is a transfer tube for use with an airfoil of a gas turbine engine coupled to a platform. The transfer tube includes a main body having a first end defining an inlet configured to receive a flow of fluid and a second end defining an outlet for the flow of fluid, the main body having a curved section. The transfer tube also includes a first mating face coupled to the first end of the main body. The transfer tube also includes a second mating face coupled to the second end of the main body. At least one of the first mating face or the second mating face is configured to be coupled to a platform body of the outer diameter platform.
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公开(公告)号：US09845694B2
公开(公告)日：2017-12-19
申请号：US14693359
申请日：2015-04-22
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Benjamin F. Hagan , Ryan Alan Waite , Bryan P. Dube , Lane Thornton
CPC classification number: F01D9/065 , F01D5/147 , F01D5/186 , F01D5/187 , F01D5/188 , F01D9/041 , F05D2240/125 , F05D2240/307 , F05D2240/81 , F05D2250/75 , Y02T50/676
Abstract: An assembly for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an airfoil including a radial end, a first passageway having an outlet at the radial end, and a second passageway having an inlet at the radial end. The assembly further includes a cover having at least one turning cavity configured to direct fluid expelled from the outlet of the first passageway into the inlet of the second passageway.
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公开(公告)号：US20170321560A1
公开(公告)日：2017-11-09
申请号：US15147954
申请日：2016-05-06
Applicant: United Technologies Corporation
Inventor： Peter Balawajder , Benjamin F. Hagan , Jeffrey Michael Jacques
CPC classification number: F01D5/3007 , F01D9/02 , F01D9/042 , F01D11/00 , F01D11/005 , F01D25/243 , F01D25/246 , F05D2220/32 , F05D2240/57 , F05D2240/80 , F05D2260/941
Abstract: A vane assembly for a gas turbine engine includes an outer platform, an inner platform, a vane, and a seal. The outer platform is disposed proximate a case. The outer platform has a first rail extending towards the case. The first rail has a first face, a second face disposed opposite the first face, and a first opening extending from the first face towards the second face. The inner platform is disposed opposite the outer platform. The vane extends between the inner platform and the outer platform. The seal is received within a slotted region that is disposed between the first face and the second face.
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Patent Agency Ranking
公开(公告)号：US20170268366A1
公开(公告)日：2017-09-21
申请号：US15071320
申请日：2016-03-16
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Michael G. McCaffrey , Peter Balawajder , David Richard Griffin , Benjamin F. Hagan
Abstract: A blade outer air seal support includes, at least one arc body having a first portion and a second portion, a blade outer air seal mounting region defined at least partially between the first portion and the second portion, and an interface feature interfacing the first portion and the second portion. The interface feature is configured such that axially aligned forces are communicated between the first and second portions through the interface feature, bypassing the blade outer air seal mounting region.
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公开(公告)号：US20160312632A1
公开(公告)日：2016-10-27
申请号：US14693359
申请日：2015-04-22
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Benjamin F. Hagan , Ryan Alan Waite , Bryan P. Dube , Lane Thornton
IPC: F01D9/06
CPC classification number: F01D9/065 , F01D5/147 , F01D5/186 , F01D5/187 , F01D5/188 , F01D9/041 , F05D2240/125 , F05D2240/307 , F05D2240/81 , F05D2250/75 , Y02T50/676
Abstract: An assembly for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an airfoil including a radial end, a first passageway having an outlet at the radial end, and a second passageway having an inlet at the radial end. The assembly further includes a cover having at least one turning cavity configured to direct fluid expelled from the outlet of the first passageway into the inlet of the second passageway.
Abstract translation: 根据本公开的示例性方面的用于燃气涡轮发动机的组件包括除了别的以外的包括径向端部的翼型件，在径向端部处具有出口的第一通道和在径向处具有入口的第二通道 结束。 组件还包括具有至少一个转动腔的盖，该转动腔构造成将从第一通道的出口排出的流体引导到第二通道的入口中。
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公开(公告)号：US09327368B2
公开(公告)日：2016-05-03
申请号：US13628298
申请日：2012-09-27
Applicant: United Technologies Corporation
Inventor： Benjamin F. Hagan
CPC classification number: B23P15/04 , F01D9/065 , F01D11/001 , F01D11/005 , F01D11/04 , F01D11/10 , F02C7/28 , F05D2240/11 , F05D2250/191 , F05D2260/30 , Y10T29/49336
Abstract: A vane assembly has a vane including an inner platform with a mount rail extending radially inwardly toward an engine center axis. An air seal is attached to the inner platform. The air seal has a single-piece ring extending circumferentially about the engine center axis. A ring nut secures the air seal to the inner platform. A biasing member cooperates with the ring nut and air seal to seal fore and aft locations on the vane.
Abstract translation: 叶片组件具有叶片，叶片包括具有径向向内朝向发动机中心轴线延伸的安装轨道的内平台。 空气密封件附接到内平台。 空气密封件具有围绕发动机中心轴线周向延伸的单件环。 环形螺母将空气密封件固定到内部平台。 偏置构件与环形螺母和空气密封件协作以密封叶片上的前后位置。
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公开(公告)号：US10738643B2
公开(公告)日：2020-08-11
申请号：US16164958
申请日：2018-10-19
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Michael G. McCaffrey , Benjamin F. Hagan , David Richard Griffin
Abstract: A seal assembly includes a seal arc segment defining first and second seal supports with a carriage defining first and second support members. The first support member supports the seal arc segment in a first ramped interface, and the second support member supports the seal arc segment in a second ramped interface. A spring is configured to bias the seal arc segment axially. A heat shield is radially inward of the spring.
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公开(公告)号：US10465543B2
公开(公告)日：2019-11-05
申请号：US15810279
申请日：2017-11-13
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Benjamin F. Hagan , Ryan Alan Waite , Bryan P. Dube , Lane Thornton
Abstract: An assembly for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an airfoil including a radial end, a first passageway having an outlet at the radial end, and a second passageway having an inlet at the radial end. The assembly further includes a cover having at least one turning cavity configured to direct fluid expelled from the outlet of the first passageway into the inlet of the second passageway.
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