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公开(公告)号：US20180361284A1
公开(公告)日：2018-12-20
申请号：US15627809
申请日：2017-06-20
Applicant: United Technologies Corporation
CPC classification number: B01D35/28 , B01D35/02 , B01D46/2403 , F01D25/32 , F02C7/05 , F02C7/055 , F03B11/00 , F05D2260/607
Abstract: A gas turbine engine includes an engine static structure that provides a flow path. A metering hole is provided in the engine static structure. A strainer is arranged over the metering hole. The strainer includes multiple holes that have a total area that is greater than a metering hole area.
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公开(公告)号：US20170268369A1
公开(公告)日：2017-09-21
申请号：US15071485
申请日：2016-03-16
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Michael G. McCaffrey , Benjamin F. Hagan , David Richard Griffin , Peter Balawajder , Christopher Corcoran
CPC classification number: F01D11/08 , F01D5/02 , F01D9/04 , F01D25/24 , F01D25/246 , F05D2220/32 , F05D2230/60 , F05D2240/11 , F05D2240/55 , F05D2260/231 , F05D2300/10 , Y02T50/672 , Y02T50/675
Abstract: A seal assembly includes a seal arc segment that defines radially inner and outer sides with the radially outer side including radially-extending sidewalls. A radially inner surface joins the radially-extending sidewalls. The radially-extending sidewalls and the radially inner surface define a pocket. A rail shield has radially-extending walls lines the radially-extending sidewalls.
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公开(公告)号：US20170002675A1
公开(公告)日：2017-01-05
申请号：US14790076
申请日：2015-07-02
Applicant: United Technologies Corporation
Inventor： Paul M. Lutjen , Christopher William Moore , David Richard Griffin
CPC classification number: F01D11/08 , F01D9/02 , F01D9/042 , F01D11/001 , F01D11/005 , F01D11/122 , F01D25/246 , F02C7/28
Abstract: A gas turbine engine assembly includes a shield that has a first portion and a second portion. The first portion extends radially from an axial end portion of the shield and includes a blade outer air seal contact surface. The second portion extends axially from a radially outer end of the first portion and includes a vane contact surface.
Abstract translation: 燃气涡轮发动机组件包括具有第一部分和第二部分的护罩。 第一部分从护罩的轴向端部径向延伸并且包括叶片外部空气密封接触表面。 第二部分从第一部分的径向外端轴向延伸并且包括叶片接触表面。
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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：US10385716B2
公开(公告)日：2019-08-20
申请号：US14790076
申请日：2015-07-02
Applicant: United Technologies Corporation
Inventor： Paul M. Lutjen , Christopher William Moore , David Richard Griffin
Abstract: A gas turbine engine assembly includes a shield that has a first portion and a second portion. The first portion extends radially from an axial end portion of the shield and includes a blade outer air seal contact surface. The second portion extends axially from a radially outer end of the first portion and includes a vane contact surface.
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Patent Agency Ranking
公开(公告)号：US20190178097A1
公开(公告)日：2019-06-13
申请号：US16161194
申请日：2018-10-16
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Michael S. Stevens , David Richard Griffin
Abstract: A support ring for a gas turbine engine includes a main body portion extending circumferentially about a center axis, a radially extending portion extending radially inward from the main body portion and having a plurality of openings, and a plurality of anti-rotation tabs extending radially inward from the main body portion and axially spaced from the radially extending portion.
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公开(公告)号：US20170268371A1
公开(公告)日：2017-09-21
申请号：US15071439
申请日：2016-03-16
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：US20170268362A1
公开(公告)日：2017-09-21
申请号：US15071281
申请日：2016-03-16
Applicant: United Technologies Corporation
Inventor： Michael G. McCaffrey , Benjamin F. Hagan , David Richard Griffin
CPC classification number: F01D11/08 , F01D9/065 , F01D11/001 , F01D11/02 , F01D11/24 , F01D25/12 , F02C7/28 , F05D2220/32 , F05D2240/11 , F05D2240/55 , F05D2260/201 , F05D2300/10 , Y02T50/672 , Y02T50/675
Abstract: A blades outer air seal includes a seal arc segment that defines radially inner and outer sides. The radially outer side includes radially-extending sidewalls and a radially inner surface that joins the radially-extending sidewalls. The radially-extending sidewalls and the radially inner surface define a pocket. A manifold is disposed at least partially in the pocket. The manifold subdivides the pocket such that there is a manifold chamber bounded by the manifold and the radially inner surface. The manifold includes at least one inlet and a plurality of outlets.
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9.发明申请公开(公告)号：US20190048796A1
公开(公告)日：2019-02-14
申请号：US16048738
申请日：2018-07-30
Applicant: United Technologies Corporation
Inventor： Walter A. Ledwith, Jr. , Scott A. Carr , Christopher J. Hanlon , Peter A. White , Theodore W. Hall , John R. Farris , Andrew S. Miller , Christopher W. Robak , David C. Pimenta , David Richard Griffin
Abstract: A method of assembling a gas turbine engine includes setting a build clearance at assembly in response to a running tip clearance defined with a cooled cooling air. A method of operating a gas turbine engine includes supplying a cooled cooling air to a high pressure turbine in response to an engine rotor speed.
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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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