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公开(公告)号：US10458264B2
公开(公告)日：2019-10-29
申请号：US14704278
申请日：2015-05-05
Applicant: United Technologies Corporation
Inventor： Dominic J. Mongillo, Jr. , Brandon W. Spangler , Lane Thornton
Abstract: A component for a gas turbine engine according to an example of the present disclosure includes, among other things, a body including a cold side surface adjacent to a mate face. A plurality of ridges extends from the cold side surface. A seal member abuts the plurality of ridges to define a plurality of cooling passages. The seal member is configured to move between a first position and a second position relative to the plurality of ridges. Each of the plurality of cooling passages includes a first inlet defined at the first position and a second, different inlet defined at the second position. A method of sealing between adjacent components of a gas turbine engine is also disclosed.
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公开(公告)号：US20190211691A1
公开(公告)日：2019-07-11
申请号：US16353563
申请日：2019-03-14
Applicant: United Technologies Corporation
Inventor： Lane Thornton , Thomas N. Slavens
CPC classification number: F01D5/186 , F01D5/187 , F01D5/28 , F02C3/04 , F02C7/12 , F05D2220/32 , F05D2240/303 , F05D2240/304 , F05D2260/201 , F05D2260/202 , F05D2300/175 , F05D2300/505 , Y02T50/676
Abstract: In one example embodiment, a blade includes an attachment region, an airfoil extending from the attachment region, and a blade cooling arrangement. The blade cooling arrangement includes at least a first feed passage disposed through the attachment region, which is connected to a first cooling passage disposed in the airfoil. A passively actuated first coolant valve is disposed in or proximate the first feed passage. A plurality of such blades can be disposed in a turbine section of an engine.
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公开(公告)号：US10005123B2
公开(公告)日：2018-06-26
申请号：US15022745
申请日：2014-09-26
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Lane Thornton , San Quach , Steven Bruce Gautschi
Abstract: In a featured embodiment, a lost core assembly includes a ceramic component having a tapered shape in a radial direction. A refractory metal component extends radially from the ceramic core component. A method of molding a gas turbine engine component is also disclosed.
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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：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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Patent Agency Ranking
26.发明申请公开(公告)号：US20160208620A1
公开(公告)日：2016-07-21
申请号：US14915455
申请日：2014-08-27
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Charles Thistle , Lane Thornton
IPC: F01D5/18
CPC classification number: F01D5/187 , F05D2220/32 , F05D2240/304 , F05D2260/2212 , F05D2260/22141 , Y02T50/676
Abstract: A gas turbine engine component includes spaced apart walls that extend in a load direction and provide a cooling passage. The cooling passage provides a tortuous passage having a generally straight portion that extends in the load direction and a bend transverse to the load direction. Elongated turbulators protrude from at least one of the walls and extend substantially in the load direction. The elongated turbulators are substantially within the generally straight portion.
Abstract translation: 燃气涡轮发动机部件包括在负载方向上延伸并提供冷却通道的间隔开的壁。 冷却通道提供具有在负载方向上延伸的大致直的部分和横向于负载方向的弯曲的曲折通道。 细长的湍流器从至少一个壁突出并基本上在负载方向上延伸。 细长的湍流器基本上在大致直的部分内。
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公开(公告)号：US11781439B2
公开(公告)日：2023-10-10
申请号：US16571678
申请日：2019-09-16
Applicant: United Technologies Corporation
Inventor： Dominic J. Mongillo, Jr. , Brandon W. Spangler , Lane Thornton
CPC classification number: F01D11/006 , F01D11/005 , F01D25/246 , F05D2240/11 , F05D2240/57 , F05D2250/182 , Y02T50/60
Abstract: A component for a gas turbine engine according to an example of the present disclosure includes, among other things, a body including a cold side surface adjacent to a mate face. A plurality of ridges extends from the cold side surface. A seal member abuts the plurality of ridges to define a plurality of cooling passages. The seal member is configured to move between a first position and a second position relative to the plurality of ridges. Each of the plurality of cooling passages includes a first inlet defined at the first position and a second, different inlet defined at the second position. A method of sealing between adjacent components of a gas turbine engine is also disclosed.
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公开(公告)号：US20210062667A1
公开(公告)日：2021-03-04
申请号：US16571678
申请日：2019-09-16
Applicant: United Technologies Corporation
Inventor： Dominic J. Mongillo, JR. , Brandon W. Spangler , Lane Thornton
Abstract: A component for a gas turbine engine according to an example of the present disclosure includes, among other things, a body including a cold side surface adjacent to a mate face. A plurality of ridges extends from the cold side surface. A seal member abuts the plurality of ridges to define a plurality of cooling passages. The seal member is configured to move between a first position and a second position relative to the plurality of ridges. Each of the plurality of cooling passages includes a first inlet defined at the first position and a second, different inlet defined at the second position. A method of sealing between adjacent components of a gas turbine engine is also disclosed.
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公开(公告)号：US10370979B2
公开(公告)日：2019-08-06
申请号：US14948511
申请日：2015-11-23
Applicant: United Technologies Corporation
Inventor： Lane Thornton
Abstract: An airfoil according to an example of the present disclosure includes, among other things, an airfoil body defining a cavity, and a baffle including a baffle body including sidewalls and defining an internal passage for conveying coolant. The baffle body is situated in the cavity such that a majority of external surfaces of the sidewalls abut the cavity.
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公开(公告)号：US10259039B2
公开(公告)日：2019-04-16
申请号：US14766061
申请日：2014-01-16
Applicant: United Technologies Corporation
Inventor： Thomas N. Slavens , Lane Thornton , Sasha M. Moore , Nicholas M. LoRicco
Abstract: A method of manufacturing a component that includes providing a core structure, casting a component about the core structure, removing a first portion of the core structure from the cast component, and leaving a second portion of the core structure in the cast component to provide a reduced cross-section in the cast component.
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