Patents by Inventor Graham Ryan Philbrick
Graham Ryan Philbrick has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Patent number: 10914187Abstract: An active clearance control manifold assembly includes multiple arcuate manifold segments each having multiple circumferential channels axially spaced apart from one another. The circumferential channels include cooling holes facing radially inward. A tube at least partially circumscribes and fluidly interconnects the manifold segments.Type: GrantFiled: September 11, 2017Date of Patent: February 9, 2021Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Jonathan Jeffery Eastwood, Joseph F. Englehart, Graham Ryan Philbrick, ChaiDee Woods Brown
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Patent number: 10612466Abstract: A turbine section for a gas turbine engine includes blade outer air seals and stator vanes that provide a core flow path. A turbine case supports blade outer air seals and stator vanes. An annular cavity is provided between an interior surface of the turbine case and the blade outer air seals and the stator vanes. A hole extends through the turbine case from an exterior surface to the interior surface. The annular cavity extends axially to an exit. A manifold circumscribes the exterior surface of the turbine case and provides an annular space therebetween. The annular space is in fluid communication with the exit of the annular cavity via the hole.Type: GrantFiled: September 11, 2017Date of Patent: April 7, 2020Assignee: United Technologies CorporationInventors: Jonathan Jeffery Eastwood, Joseph F. Englehart, Graham Ryan Philbrick, Henry K. Webster, Richard Seleski, ChaiDee Woods Brown, Michael G. McCaffrey
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Patent number: 10415421Abstract: 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.Type: GrantFiled: February 6, 2017Date of Patent: September 17, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Jason Arnold, Graham Ryan Philbrick, Patrick D. Couture
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Patent number: 10280783Abstract: A turbomachine seal plate includes a substrate with a first material that defines a surface having a substrate width. The substrate includes a first terminus extension that is raised and extends from a terminus portion of the substrate. The first terminus extension extends outwardly relative to the surface up to a terminus extension height. The turbomachine seal plate also includes a coating having a second material that covers the surface of the substrate and defines a coating width. The coating abuts a side of the first terminus extension. The coating width can be substantially equal to the terminus extension height.Type: GrantFiled: November 7, 2014Date of Patent: May 7, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Graham Ryan Philbrick, Ken Robert Lagueux
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Patent number: 10247029Abstract: A gas turbine engine, system, and method with clearance control are provided. For example, the gas turbine engine includes a static component, and a rotating component that shifts axially in one of an aft direction and a forward direction in relation to the static component during a first operating condition of the gas turbine engine, and shifts axially in the other of the aft direction and the forward direction in relation to the static component during a second operating condition of the gas turbine engine. The first operating condition is when a rotating component growth and a static component growth change at different rates. The second operating condition is when the rotating component growth and static component growth normalize.Type: GrantFiled: February 4, 2016Date of Patent: April 2, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Graham Ryan Philbrick, Allison Zywiak
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Publication number: 20190078514Abstract: A turbine section for a gas turbine engine includes blade outer air seals and stator vanes that provide a core flow path. A turbine case supports blade outer air seals and stator vanes. An annular cavity is provided between an interior surface of the turbine case and the blade outer air seals and the stator vanes. A hole extends through the turbine case from an exterior surface to the interior surface. The annular cavity extends axially to an exit. A manifold circumscribes the exterior surface of the turbine case and provides an annular space therebetween. The annular space is in fluid communication with the exit of the annular cavity via the hole.Type: ApplicationFiled: September 11, 2017Publication date: March 14, 2019Inventors: Jonathan Jeffery Eastwood, Joseph F. Englehart, Graham Ryan Philbrick, Henry K. Webster, Richard Seleski, ChaiDee Woods Brown, Michael G. McCaffrey
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Publication number: 20190078458Abstract: An active clearance control manifold assembly includes multiple arcuate manifold segments each having multiple circumferential channels axially spaced apart from one another. The circumferential channels include cooling holes facing radially inward. A tube at least partially circumscribes and fluidly interconnects the manifold segments.Type: ApplicationFiled: September 11, 2017Publication date: March 14, 2019Inventors: Jonathan Jeffery Eastwood, Joseph F. Englehart, Graham Ryan Philbrick, ChaiDee Woods Brown
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Publication number: 20190078459Abstract: A method of controlling a power turbine running clearance between blade tips and a case structure. The method includes the step of adjusting an active clearance control system fluid flow based upon a power turbine speed to obtain a desired running clearance in a power turbine.Type: ApplicationFiled: September 11, 2017Publication date: March 14, 2019Inventors: Jonathan Jeffery Eastwood, Joseph F. Englehart, Graham Ryan Philbrick
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Publication number: 20180223684Abstract: 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.Type: ApplicationFiled: February 6, 2017Publication date: August 9, 2018Inventors: Jason Arnold, Graham Ryan Philbrick, Patrick D. Couture
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Patent number: 9797260Abstract: A gas turbine engine component according to an exemplary aspect of this disclosure includes a peripheral portion defining an internal cooling passage and a recess in fluid communication with the internal cooling passage. The peripheral portion includes an outer wear surface, and the recess tapers toward the outer wear surface.Type: GrantFiled: April 23, 2015Date of Patent: October 24, 2017Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Graham Ryan Philbrick, Ken Lagueux, Bret M. Teller
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Publication number: 20170226886Abstract: A gas turbine engine, system, and method with clearance control are provided. For example, the gas turbine engine includes a static component, and a rotating component that shifts axially in one of an aft direction and a forward direction in relation to the static component during a first operating condition of the gas turbine engine, and shifts axially in the other of the aft direction and the forward direction in relation to the static component during a second operating condition of the gas turbine engine. The first operating condition is when a rotating component growth and a static component growth change at different rates. The second operating condition is when the rotating component growth and static component growth normalize.Type: ApplicationFiled: February 4, 2016Publication date: August 10, 2017Inventors: Graham Ryan Philbrick, Allison Zywiak
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Patent number: 9719364Abstract: 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.Type: GrantFiled: February 4, 2015Date of Patent: August 1, 2017Assignee: United Technologies CorporationInventors: Graham Ryan Philbrick, Patrick D Couture
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Publication number: 20170074112Abstract: A gas turbine engine includes a conduit that is configured to direct a fluid to at least one manifold that is adjacent to a turbine section. A first intake is in fluid communication with the conduit. A second intake is in fluid communication with the conduit. A valve is configured to selectively direct a fluid from at least one of the first intake and the second intake.Type: ApplicationFiled: March 23, 2015Publication date: March 16, 2017Inventors: Graham Ryan Philbrick, Ken Lagueux
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Publication number: 20160312638Abstract: A turbomachine seal plate includes a substrate with a first material that defines a surface having a substrate width. The substrate includes a first terminus extension that is raised and extends from a terminus portion of the substrate. The first terminus extension extends outwardly relative to the surface up to a terminus extension height. The turbomachine seal plate also includes a coating having a second material that covers the surface of the substrate and defines a coating width. The coating abuts a side of the first terminus extension. The coating width can be substantially equal to the terminus extension height.Type: ApplicationFiled: November 7, 2014Publication date: October 27, 2016Inventors: Graham Ryan Philbrick, Ken Robert Lagueux
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Publication number: 20160222811Abstract: 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.Type: ApplicationFiled: February 4, 2015Publication date: August 4, 2016Inventors: Graham Ryan Philbrick, Patrick D. Couture
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Publication number: 20150308274Abstract: A gas turbine engine component according to an exemplary aspect of this disclosure includes a peripheral portion defining an internal cooling passage and a recess in fluid communication with the internal cooling passage. The peripheral portion includes an outer wear surface, and the recess tapers toward the outer wear surface.Type: ApplicationFiled: April 23, 2015Publication date: October 29, 2015Inventors: Graham Ryan Philbrick, Ken Lagueux, Bret M. Teller