Patents by Inventor Terence P. Tyler, JR.
Terence P. Tyler, JR. 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: 10487678Abstract: A gas turbine engine includes a stator vane. A blade outer air seal may be adjacent to the stator vane. A seal assembly may be disposed between the blade outer air seal and the stator vane. The seal assembly may include a first seal disposed between a first airflow path and a second airflow path. A second seal may be disposed between the first airflow path and the second airflow path. The second seal may be disposed in a series arrangement with the first seal.Type: GrantFiled: May 23, 2016Date of Patent: November 26, 2019Assignee: United Technologies CorporationInventors: Terence P. Tyler, Jr., Timothy M. Davis, Jeremy Drake, Jose R. Paulino, Jaimie Schweitzer
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Patent number: 10352184Abstract: A seal assembly includes a blade outer air seal, a downstream vane, and a pressure wall, according to various embodiments. The blade outer air seal may include a radially outer surface and the downstream vane may be coupled to the blade outer air seal via a fluid sealing engagement. The pressure wall may be coupled to the blade outer air seal and may define a metering orifice. In various embodiments, the metering orifice of the pressure wall is configured to meter air flow from a first plenum upstream of the pressure wall to a second plenum downstream of the pressure wall. In various embodiments, at least a preponderance of the radially outer surface of the blade outer air seal at least partially defines the first plenum and the fluid sealing engagement at least partially defines the second plenum.Type: GrantFiled: October 31, 2016Date of Patent: July 16, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Jose R. Paulino, Ken F. Blaney, Terence P. Tyler, Jr., Daniel S. Rogers, Anthony B. Swift, Thomas E. Clark
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Patent number: 10309253Abstract: A blade outer air seal for a gas turbine engine includes a gas path surface exposed to exhaust gas flow, a first side extending radially outward from the gas path surface, a second side extending radially outward from the gas path surface, and a plurality of film cooling holes disposed on at least one of the gas path surface. The first side and the second side, the film cooling holes are disposed at locations described by a set of Cartesian coordinates set forth in Table 1. The Cartesian coordinates are provided by an axial coordinate, a circumferential coordinate and a radial coordinate relative to a defined point of origin. A gas turbine engine is also disclosed.Type: GrantFiled: January 13, 2016Date of Patent: June 4, 2019Assignee: United Technologies CorporationInventors: Kevin J. Ryan, Terence P. Tyler, Jr., Ken F. Blaney
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Patent number: 10167957Abstract: A metal gasket bellows seal includes a first ply comprised of a first material having a first yield strength. The metal gasket bellows seal also includes a second ply positioned adjacent to the first ply and comprised of a second material having a second yield strength that is less than the first yield strength.Type: GrantFiled: May 31, 2016Date of Patent: January 1, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Timothy M. Davis, Terence P. Tyler, Jr., Jose R. Paulino, Paul M. Lutjen
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Patent number: 10036271Abstract: A blade outer air seal for a gas turbine engine includes a gas path surface exposed to exhaust gas flow, a first side extending radially outward from the gas path surface, a second side extending radially outward from the gas path surface, and a plurality of film cooling holes disposed on at least one of the gas path surface. The first side and the second side, the film cooling holes are disposed at locations described by a set of Cartesian coordinates set forth in Table 1. The Cartesian coordinates are provided by an axial coordinate, a circumferential coordinate and a radial coordinate relative to a defined point of origin. A gas turbine engine is also disclosed.Type: GrantFiled: January 13, 2016Date of Patent: July 31, 2018Assignee: United Technologies CorporationInventors: Kevin J. Ryan, Terence P. Tyler, Jr., Ken F. Blaney
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Publication number: 20180119560Abstract: A seal assembly includes a blade outer air seal, a downstream vane, and a pressure wall, according to various embodiments. The blade outer air seal may include a radially outer surface and the downstream vane may be coupled to the blade outer air seal via a fluid sealing engagement. The pressure wall may be coupled to the blade outer air seal and may define a metering orifice. In various embodiments, the metering orifice of the pressure wall is configured to meter air flow from a first plenum upstream of the pressure wall to a second plenum downstream of the pressure wall. In various embodiments, at least a preponderance of the radially outer surface of the blade outer air seal at least partially defines the first plenum and the fluid sealing engagement at least partially defines the second plenum.Type: ApplicationFiled: October 31, 2016Publication date: May 3, 2018Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Jose R. Paulino, Ken F. Blaney, Terence P. Tyler, JR., Daniel S. Rogers, Anthony B. Swift, Thomas E. Clark
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Publication number: 20170343112Abstract: A metal gasket bellows seal includes a first ply comprised of a first material having a first yield strength. The metal gasket bellows seal also includes a second ply positioned adjacent to the first ply and comprised of a second material having a second yield strength that is less than the first yield strength.Type: ApplicationFiled: May 31, 2016Publication date: November 30, 2017Inventors: TIMOTHY M. DAVIS, Terence P. Tyler, JR., Jose R. Paulino, Paul M. Lutjen
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Publication number: 20170335705Abstract: A gas turbine engine includes a stator vane. A blade outer air seal may be adjacent to the stator vane. A seal assembly may be disposed between the blade outer air seal and the stator vane. The seal assembly may include a first seal disposed between a first airflow path and a second airflow path. A second seal may be disposed between the first airflow path and the second airflow path. The second seal may be disposed in a series arrangement with the first seal.Type: ApplicationFiled: May 23, 2016Publication date: November 23, 2017Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Terence P. Tyler, JR., Timothy M. Davis, Jeremy Drake, Jose R. Paulino, Jaimie Schweitzer
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Patent number: 9708922Abstract: A seal assembly includes a first component, a second component, a first seal, a first shelf, a second shelf, and a second seal. The second component is adjacent to the first component and forms a cavity between the first and second components. The first seal spans the cavity. The first shelf extends axially from the first component and is located between the first seal and a hot gas path. The second shelf extends axially from the second component and is located between the first shelf and the hot gas path; the second shelf together with the first shelf forms a flow channel. The second seal conforms to the first shelf, sealing the flow channel.Type: GrantFiled: May 23, 2016Date of Patent: July 18, 2017Assignee: United Technologies CorporationInventors: Timothy M. Davis, Mark J. Rogers, Paul M. Lutjen, Terence P. Tyler, Jr., Michael J. Bruskotter
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Publication number: 20170198599Abstract: A blade outer air seal for a gas turbine engine includes a gas path surface exposed to exhaust gas flow, a first side extending radially outward from the gas path surface, a second side extending radially outward from the gas path surface, and a plurality of film cooling holes disposed on at least one of the gas path surface. The first side and the second side, the film cooling holes are disposed at locations described by a set of Cartesian coordinates set forth in Table 1. The Cartesian coordinates are provided by an axial coordinate, a circumferential coordinate and a radial coordinate relative to a defined point of origin. A gas turbine engine is also disclosed.Type: ApplicationFiled: January 13, 2016Publication date: July 13, 2017Inventors: Kevin J. Ryan, Terence P. Tyler, JR., Ken F. Blaney
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Publication number: 20170198603Abstract: A blade outer air seal for a gas turbine engine includes a gas path surface exposed to exhaust gas flow, a first side extending radially outward from the gas path surface, a second side extending radially outward from the gas path surface, and a plurality of film cooling holes disposed on at least one of the gas path surface. The first side and the second side, the film cooling holes are disposed at locations described by a set of Cartesian coordinates set forth in Table 1. The Cartesian coordinates are provided by an axial coordinate, a circumferential coordinate and a radial coordinate relative to a defined point of origin. A gas turbine engine is also disclosed.Type: ApplicationFiled: January 13, 2016Publication date: July 13, 2017Inventors: Kevin J. Ryan, Terence P. Tyler, JR., Ken F. Blaney