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Patent Agency Ranking
公开(公告)号：US10415421B2
公开(公告)日：2019-09-17
申请号：US15425689
申请日：2017-02-06
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Jason Arnold , Graham Ryan Philbrick , Patrick D. Couture
Abstract: Disclosed is an active tip clearance control system (ATCCS) for a gas turbine engine, having an electronically controlled regulating valve directing cooling airflow to a turbine case, and an engine electronic control (EEC), controlling the electronically controlled regulating valve, wherein the EEC controls the electronically controlled regulating valve to regulate cooling airflow according to a selected target blade tip clearance schedule, and wherein the selected target blade tip clearance schedule is selected before or after an engine cycle, from of a plurality of target blade tip clearance schedules, each correlating to one of a plurality of thrust rating applications for the engine.
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公开(公告)号：US10344614B2
公开(公告)日：2019-07-09
申请号：US15096346
申请日：2016-04-12
Applicant: United Technologies Corporation
Inventor： Graham R. Philbrick , Patrick D. Couture , Jason Arnold
Abstract: Aspects of the disclosure are directed to systems and methods for receiving operating state parameters associated with an operative state of an aircraft, determining a clearance value between a first structure of the engine and a second structure of the engine, where the clearance value is determined based on the operating state parameters and a passive clearance model that includes a specification of an uncertainty in the clearance value, determining that the clearance value deviates from a clearance target in an amount that is greater than a threshold, and engaging an active clearance control (ACC) mechanism based on the deviation.
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公开(公告)号：US20180223684A1
公开(公告)日：2018-08-09
申请号：US15425689
申请日：2017-02-06
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Jason Arnold , Graham Ryan Philbrick , Patrick D. Couture
Abstract: Disclosed is an active tip clearance control system (ATCCS) for a gas turbine engine, having an electronically controlled regulating valve directing cooling airflow to a turbine case, and an engine electronic control (EEC), controlling the electronically controlled regulating valve, wherein the EEC controls the electronically controlled regulating valve to regulate cooling airflow according to a selected target blade tip clearance schedule, and wherein the selected target blade tip clearance schedule is selected before or after an engine cycle, from of a plurality of target blade tip clearance schedules, each correlating to one of a plurality of thrust rating applications for the engine.
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公开(公告)号：US09833869B2
公开(公告)日：2017-12-05
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.
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公开(公告)号：US20170292399A1
公开(公告)日：2017-10-12
申请号：US15096346
申请日：2016-04-12
Applicant: United Technologies Corporation
Inventor： Graham R. Philbrick , Patrick D. Couture , Jason Arnold
CPC classification number: F01D17/145 , B64D27/10 , F01D5/02 , F01D11/24 , F01D25/24 , F05D2220/323 , F05D2270/114 , F05D2270/20 , F05D2270/303 , F05D2270/304 , F05D2270/305 , F05D2270/309 , F05D2270/335 , F05D2270/44
Abstract: Aspects of the disclosure are directed to systems and methods for receiving operating state parameters associated with an operative state of an aircraft, determining a clearance value between a first structure of the engine and a second structure of the engine, where the clearance value is determined based on the operating state parameters and a passive clearance model that includes a specification of an uncertainty in the clearance value, determining that the clearance value deviates from a clearance target in an amount that is greater than a threshold, and engaging an active clearance control (ACC) mechanism based on the deviation.
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