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公开(公告)号：US10801331B2
公开(公告)日：2020-10-13
申请号：US15175108
申请日：2016-06-07
Applicant: United Technologies Corporation
Inventor： Patrick D. Couture , Scott D. Lewis , Kyle C. Lana
Abstract: A gas turbine engine blade includes a blade portion having a leading edge and a trailing edge. A first surface connects the leading edge to the trailing edge and a second surface connects the leading edge to the trailing edge. A tip section is located at a first end of the blade portion and includes a pocket protruding into the tip section from an outermost end of the tip section. The pocket has a first side wall adjacent the first surface and a second side wall adjacent the second surface. At least one of the first side wall and the second side wall have a curve distinct from a curve of the corresponding adjacent surface.
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公开(公告)号：US09810091B2
公开(公告)日：2017-11-07
申请号：US14823568
申请日：2015-08-11
Applicant: United Technologies Corporation
Inventor： Kevin Zacchera , Patrick D. Couture
CPC classification number: F01D21/003 , F01D5/225 , F01D11/20 , F05D2220/30 , F05D2240/11 , F05D2260/81 , F05D2260/83 , F05D2270/20 , F05D2270/44 , F05D2270/71
Abstract: A method is provided for calibrating an active clearance control system for a plurality of turbine engines. During this method, a squeeze test is performed between a tip of a rotor blade and a shroud. Results of the squeeze test are applied to adjust a gap between the tip and the shroud. The performance of the squeeze test and the application of the results may be individually performed for each of the turbine engines.
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公开(公告)号：US11473510B2
公开(公告)日：2022-10-18
申请号：US16388227
申请日：2019-04-18
Applicant: United Technologies Corporation
Inventor： Joseph Kehoe , Richard P. Meisner , Manuj Dhingra , Patrick D. Couture , Matthew R. Feulner , Brenda J. Lisitano , Christopher L. Ho
Abstract: A method of operating a gas turbine engine includes commanding an acceleration of the gas turbine engine and moving a variable pitch high pressure compressor vane toward an open position thereby reducing an acceleration rate of a high pressure turbine rotor thereby reducing a change in a clearance gap between the high pressure turbine rotor and a blade outer airseal. An active clearance control system of a gas turbine engine includes an engine control system configured to command an acceleration of the gas turbine engine and move a variable pitch high pressure compressor vane toward an open position thereby slowing an acceleration rate of a high pressure turbine rotor thereby reducing a change in a clearance gap between the high pressure turbine rotor and a blade outer airseal located radially outboard of the high pressure turbine rotor.
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公开(公告)号：US20170350255A1
公开(公告)日：2017-12-07
申请号：US15175108
申请日：2016-06-07
Applicant: United Technologies Corporation
Inventor： Patrick D. Couture , Scott D. Lewis , Kyle C. Lana
Abstract: A gas turbine engine blade includes a blade portion having a leading edge and a trailing edge. A first surface connects the leading edge to the trailing edge and a second surface connects the leading edge to the trailing edge. A tip section is located at a first end of the blade portion and includes a pocket protruding into the tip section from an outermost end of the tip section. The pocket has a first side wall adjacent the first surface and a second side wall adjacent the second surface. At least one of the first side wall and the second side wall have a curve distinct from a curve of the corresponding adjacent surface.
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公开(公告)号：US20200332726A1
公开(公告)日：2020-10-22
申请号：US16388227
申请日：2019-04-18
Applicant: United Technologies Corporation
Inventor： Joseph Kehoe , Richard P. Meisner , Manuj Dhingra , Patrick D. Couture , Matthew R. Feulner , Brenda J. Lisitano , Christopher L. Ho
IPC: F02C9/54
Abstract: A method of operating a gas turbine engine includes commanding an acceleration of the gas turbine engine and moving a variable pitch high pressure compressor vane toward an open position thereby reducing an acceleration rate of a high pressure turbine rotor thereby reducing a change in a clearance gap between the high pressure turbine rotor and a blade outer airseal. An active clearance control system of a gas turbine engine includes an engine control system configured to command an acceleration of the gas turbine engine and move a variable pitch high pressure compressor vane toward an open position thereby slowing an acceleration rate of a high pressure turbine rotor thereby reducing a change in a clearance gap between the high pressure turbine rotor and a blade outer airseal located radially outboard of the high pressure turbine rotor.
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Patent Agency Ranking
公开(公告)号：US10702964B2
公开(公告)日：2020-07-07
申请号：US15830450
申请日：2017-12-04
Applicant: United Technologies Corporation
Inventor： Paul M. Lutjen , Patrick D. Couture
Abstract: A blade outer air seal for a gas turbine engine having a surface that is eccentric with respect to the engine rotation centerline, and a method for creating same, are disclosed. Also, a method for grinding a work piece having nominal curvature defined by a work piece curvature centerline is disclosed, comprising the steps of: a) determining a desired surface profile for the work piece; b) providing a rotating grinding surface having a grinding rotation centerline; c) offsetting the grinding rotation centerline from the work piece curvature centerline; and d) applying the rotating grinding surface to the work piece while rotating the rotating grinding surface about the grinding rotation centerline to create the desired surface profile.
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公开(公告)号：US20160047269A1
公开(公告)日：2016-02-18
申请号：US14823568
申请日：2015-08-11
Applicant: United Technologies Corporation
Inventor： Kevin Zacchera , Patrick D. Couture
CPC classification number: F01D21/003 , F01D5/225 , F01D11/20 , F05D2220/30 , F05D2240/11 , F05D2260/81 , F05D2260/83 , F05D2270/20 , F05D2270/44 , F05D2270/71
Abstract: A method is provided for calibrating an active clearance control system for a plurality of turbine engines. During this method, a squeeze test is performed between a tip of a rotor blade and a shroud. Results of the squeeze test are applied to adjust a gap between the tip and the shroud. The performance of the squeeze test and the application of the results may be individually performed for each of the turbine engines.
Abstract translation: 提供了一种用于校准多个涡轮发动机的主动间隙控制系统的方法。 在该方法中，在转子叶片的尖端和护罩之间进行挤压试验。 应用挤压试验的结果来调整尖端和护罩之间的间隙。 挤压试验的性能和结果的应用可以针对每个涡轮发动机单独执行。
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公开(公告)号：US20180085880A1
公开(公告)日：2018-03-29
申请号：US15830450
申请日：2017-12-04
Applicant: United Technologies Corporation
Inventor： Paul M. Lutjen , Patrick D. Couture
Abstract: A blade outer air seal for a gas turbine engine having a surface that is eccentric with respect to the engine rotation centerline, and a method for creating same, are disclosed. Also, a method for grinding a work piece having nominal curvature defined by a work piece curvature centerline is disclosed, comprising the steps of: a) determining a desired surface profile for the work piece; b) providing a rotating grinding surface having a grinding rotation centerline; c) offsetting the grinding rotation centerline from the work piece curvature centerline; and d) applying the rotating grinding surface to the work piece while rotating the rotating grinding surface about the grinding rotation centerline to create the desired surface profile.
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公开(公告)号：US20160222811A1
公开(公告)日：2016-08-04
申请号：US14613692
申请日：2015-02-04
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Graham Ryan Philbrick , Patrick D. Couture
CPC classification number: F01D11/08 , B23Q11/005 , B24B19/26 , B24B23/08 , B24B55/10 , F01D5/005 , F01D9/02 , F01D11/10 , F01D25/12 , F01D25/24 , F01D25/246 , F05D2220/32 , F05D2230/10 , F05D2230/18 , F05D2240/55
Abstract: A process for machining a turbine engine blade outer air seal in situ, the process comprising replacing a blade with a cutting tool assembly proximate a blade outer air seal, wherein the blade outer air seal is assembled in a gas turbine engine case. The process includes coupling a blower to the blade outer air seal. The blade outer air seal comprises at least one flow path. The process includes creating a purge air stream with the blower through the blade outer air seal. The process includes machining the blade outer air seal, wherein particulate is formed from the machining. The process includes preventing the particulate from blocking the at least one flow path of the blade outer air seal.
Abstract translation: 一种用于在现场加工涡轮发动机叶片外部空气密封件的方法，该方法包括用靠近叶片外部空气密封件的切割工具组件替换叶片，其中叶片外部空气密封件组装在燃气涡轮发动机壳体中。 该过程包括将鼓风机连接到叶片外部空气密封件。 叶片外部空气密封件包括至少一个流动路径。 该方法包括通过叶片外部空气密封件与鼓风机产生吹扫空气流。 该方法包括加工叶片外部空气密封件，其中颗粒由机械加工形成。 该方法包括防止颗粒物阻塞叶片外部空气密封件的至少一个流动路径。
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公开(公告)号：US20140227087A1
公开(公告)日：2014-08-14
申请号：US14176669
申请日：2014-02-10
Applicant: United Technologies Corporation
Inventor： Paul M. Lutjen , Patrick D. Couture
CPC classification number: B24B1/00 , B24B19/26 , F01D11/12 , F05D2240/11 , F05D2250/15 , F05D2250/712 , F05D2250/73 , Y10T29/49982
Abstract: A blade outer air seal for a gas turbine engine having a surface that is eccentric with respect to the engine rotation centerline, and a method for creating same, are disclosed. Also, a method for grinding a work piece having nominal curvature defined by a work piece curvature centerline is disclosed, comprising the steps of: a) determining a desired surface profile for the work piece; b) providing a rotating grinding surface having a grinding rotation centerline; c) offsetting the grinding rotation centerline from the work piece curvature centerline; and d) applying the rotating grinding surface to the work piece while rotating the rotating grinding surface about the grinding rotation centerline to create the desired surface profile.
Abstract translation: 公开了一种用于具有相对于发动机旋转中心线偏心的表面的燃气涡轮发动机的叶片外部空气密封件及其制造方法。 此外，公开了一种用于研磨具有由工件曲率中心线限定的标称曲率的工件的方法，包括以下步骤：a）确定所述工件的期望的表面轮廓; b）提供具有研磨旋转中心线的旋转研磨表面; c）将磨削旋转中心线与工件曲率中心线相抵消; 以及d）将旋转研磨表面施加到工件上，同时使旋转的研磨表面围绕研磨旋转中心线旋转以产生所需的表面轮廓。
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