Patents by Inventor Seth J. Thomen
Seth J. Thomen 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: 10626729Abstract: An airfoil includes a cooling air passage for receiving a cooling air flow. A chevron including a first rib and a second rib extends from a common tip is disposed within the cooling passage for generating a turbulent flow to improve heat transfer. The chevron includes an angle between the first rib and the second rib that is greater than 90 degrees.Type: GrantFiled: March 13, 2014Date of Patent: April 21, 2020Assignee: United Technologies CorporationInventors: Seth J. Thomen, Edward F. Pietraszkiewicz, Dominic J. Mongillo, Jr., Wieslaw A. Chlus, Erik R. Granstrand
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Patent number: 10408066Abstract: An airfoil for a gas turbine engine includes pressure and suction walls spaced apart from one another and joined at leading and trailing edges to provide an airfoil that extends in a radial direction. The airfoil has a cooling passage arranged between the pressure and suction walls that extend toward a tip of the airfoil. The tip includes a pocket that separates the pressure and suction walls. Scarfed cooling holes fluidly connect the cooling passage to the pocket. The scarfed cooling holes include a portion that is recessed into a face of the suction wall and exposed to the pocket.Type: GrantFiled: August 15, 2012Date of Patent: September 10, 2019Assignee: United Technologies CorporationInventors: Wieslaw A. Chlus, Seth J. Thomen
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Patent number: 10215051Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a platform having a non-gas path surface and a gas path surface, a cover plate positioned relative to the non-gas path surface and a cooling passage that extends between the cover plate and the non-gas path surface. At least one cooling entrance is formed through the cover plate and configured to bias the flow of a cooling fluid toward a prioritized location of the non-gas path surface.Type: GrantFiled: August 13, 2014Date of Patent: February 26, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Seth J. Thomen, Edward Pietraszkiewicz
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Patent number: 10156150Abstract: An airfoil component for a gas turbine engine includes a platform joined to an airfoil. The platform includes a flow path surface that extends between spaced apart lateral surfaces. The airfoil extends from the flow path surface. A contoured surface adjoins the flow path surface and one of the lateral surfaces.Type: GrantFiled: March 10, 2014Date of Patent: December 18, 2018Assignee: United Technologies CorporationInventors: Wieslaw A. Chlus, Seth J. Thomen
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Patent number: 9995173Abstract: The present disclosure relates to cooling systems for turbine stators. A stator may include a vane platform. A ducting plate may be coupled to the vane platform. The ducting plate and the vane platform may form a cooling chamber between the ducting plate and the vane platform. The ducting plate may include an inlet adjacent to a leading edge of the vane platform. The vane platform may include an outlet adjacent to a trailing edge of the vane platform. The ducting plate may be configured to channel cooling air through the cooling chamber from the leading edge to the trailing edge.Type: GrantFiled: October 27, 2015Date of Patent: June 12, 2018Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Pedro L. Castaneda, Edward F. Pietraszkiewicz, Rafael A. Perez, Nestor A. Alvarez, Seth J. Thomen
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Patent number: 9982549Abstract: A gas turbine engine stage includes a rotor having a slot. A blade has a root received in the slot, and a shank that extends radially outward from the root to a platform that supports an airfoil. A seal is supported on the shank and in engagement circumferentially between and with the shank and the rotor within the slot. A gas turbine engine includes compressor and turbine sections. The turbine section has a rotor with a slot. A combustor is provided axially between the compressor and turbine sections. A turbine blade in the turbine section includes a root received in the slot and a shank that extends radially outward from the root to a platform that supports an airfoil.Type: GrantFiled: December 18, 2012Date of Patent: May 29, 2018Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Seth J. Thomen, Wieslaw A. Chlus
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Patent number: 9850761Abstract: An airfoil assembly for a gas turbine engine is disclosed and includes a platform portion defining a portion of a gas flow path and a root portion for attachment of the turbine airfoil, the root portion including a bottom surface including a bottom area and a plurality of inlets that define a total inlet area as a ratio of the inlet area to the bottom area. An airfoil extends from the platform and including a plurality of cooling air passages in communication with the plurality of inlets.Type: GrantFiled: January 24, 2014Date of Patent: December 26, 2017Assignee: United Technologies CorporationInventors: Seth J. Thomen, Wieslaw A. Chlus
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Publication number: 20160194980Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a platform having a non-gas path surface and a gas path surface, a cover plate positioned relative to the non-gas path surface and a cooling passage that extends between the cover plate and the non-gas path surface. At least one cooling entrance is formed through the cover plate and configured to bias the flow of a cooling fluid toward a prioritized location of the non-gas path surface.Type: ApplicationFiled: August 13, 2014Publication date: July 7, 2016Inventors: Seth J. THOMEN, Edward PIETRASZKIEWICZ
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Publication number: 20160169002Abstract: An airfoil according to an exemplary aspect of the present disclosure includes, among other things, an airfoil body that includes a first wall and a second wall spaced apart and joined together at each of a leading edge and a trailing edge and extending between a root and a tip. An internal cooling circuit is disposed at least partially inside of the airfoil body. The internal cooling circuit has a first cooling passage disposed near a junction between the tip and the trailing edge and a fanned array of cooling holes that extend between the first cooling passage to at least the tip.Type: ApplicationFiled: July 24, 2014Publication date: June 16, 2016Inventors: Wieslaw A. CHLUS, Seth J. THOMEN
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Publication number: 20160047271Abstract: The present disclosure relates to cooling systems for turbine stators. A stator may include a vane platform. A ducting plate may be coupled to the vane platform. The ducting plate and the vane platform may form a cooling chamber between the ducting plate and the vane platform. The ducting plate may include an inlet adjacent to a leading edge of the vane platform. The vane platform may include an outlet adjacent to a trailing edge of the vane platform. The ducting plate may be configured to channel cooling air through the cooling chamber from the leading edge to the trailing edge.Type: ApplicationFiled: October 27, 2015Publication date: February 18, 2016Applicant: United Technologies CorporationInventors: Pedro L. Castaneda, Edward F. Pietraszkiewicz, Rafael A. Perez, Nestor A. Alvarez, Seth J. Thomen
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Publication number: 20160032730Abstract: An airfoil includes a cooling air passage for receiving a cooling air flow. A chevron including a first rib and a second rib extends from a common tip is disposed within the cooling passage for generating a turbulent flow to improve heat transfer. The chevron includes an angle between the first rib and the second rib that is greater than 90 degrees.Type: ApplicationFiled: March 13, 2014Publication date: February 4, 2016Inventors: Seth J. Thomen, Edward F. Pietraszkiewicz, Dominic J. Mongillo, JR., Wieslaw A. Chlus, Erik R. Granstrand
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Patent number: 9243501Abstract: A blade for a gas turbine engine includes a shank interconnecting a root and a platform, and an airfoil extending radially from the shank. The shank includes a pocket with the platform overhanging the pocket. A rail extends axially along a lateral edge of the platform and extends radially inward from the platform in a direction opposite the airfoil. A gusset extends from an underside of the platform facing the pocket and in a circumferential direction between the rail and the shank.Type: GrantFiled: September 11, 2012Date of Patent: January 26, 2016Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Seth J. Thomen, Edward F. Pietraszkiewicz
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Patent number: 9243504Abstract: A damper pin for coupling platforms of adjacent turbine blades includes a first flat longitudinal end region, a second flat longitudinal end region and a reduced cross sectional area. The reduced cross sectional area is separated from the first flat longitudinal end region by a first main body region and the reduced cross sectional area is separated from the second flat longitudinal end region by a second main body region. The cross sectional area of the reduced cross sectional area is less than the cross sectional area of each of the first and second main body regions.Type: GrantFiled: December 30, 2013Date of Patent: January 26, 2016Assignee: United Technologies CorporationInventors: Seth J. Thomen, Christopher Corcoran
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Publication number: 20160003074Abstract: An airfoil component for a gas turbine engine includes a platform joined to an airfoil. The platform includes a flow path surface that extends between spaced apart lateral surfaces. The airfoil extends from the flow path surface. A contoured surface adjoins the flow path surface and one of the lateral surfaces.Type: ApplicationFiled: March 10, 2014Publication date: January 7, 2016Inventors: Wieslaw A. Chlus, Seth J. Thomen
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Publication number: 20150369055Abstract: An airfoil assembly for a gas turbine engine is disclosed and includes a platform portion defining a portion of a gas flow path and a root portion for attachment of the turbine airfoil, the root portion including a bottom surface including a bottom area and a plurality of inlets that define a total inlet area as a ratio of the inlet area to the bottom area. An airfoil extends from the platform and including a plurality of cooling air passages in communication with the plurality of inlets.Type: ApplicationFiled: January 24, 2014Publication date: December 24, 2015Inventors: Seth J. Thomen, Wieslaw A. Chlus
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Publication number: 20150354369Abstract: An airfoil for a gas turbine engine includes an airfoil that extends from a platform that has first and second circumferential sides that respectively extend to first and second circumferential edges. The first circumferential side has a tapered surface at a first angle relative to a flow path surface. The second circumferential surface has a cooling hole that extends toward the second lateral edge at a second angle relative to the flow path surface. The tapered surface and the cooling hole are axially aligned with one another.Type: ApplicationFiled: June 2, 2015Publication date: December 10, 2015Inventors: Wieslaw A. Chlus, Seth J. Thomen
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Patent number: 8951014Abstract: A gas turbine engine blade comprises a dovetail, a shank extending from the dovetail, an airfoil, and a platform between the shank and the airfoil. The platform comprises a side wall extending between an upstream side and a downstream side of the platform. A first pin channel extends from the upstream side of the sidewall and a second pin channel, co-axial with the first pin channel, extends from the downstream side of the sidewall. The first channel includes a radial notch at the upstream longitudinal end of the first pin channel.Type: GrantFiled: March 15, 2011Date of Patent: February 10, 2015Assignee: United Technologies CorporationInventors: Christopher Corcoran, Seth J. Thomen
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Patent number: 8876479Abstract: A damper pin for coupling platforms of adjacent turbine blades includes a first flat longitudinal end region, a second flat longitudinal end region and a reduced cross sectional area. The reduced cross sectional area is separated from the first flat longitudinal end region by a first main body region and the reduced cross sectional area is separated from the second flat longitudinal end region by a second main body region. The cross sectional area of the reduced cross sectional area is less than the cross sectional area of each of the first and second main body regions.Type: GrantFiled: March 15, 2011Date of Patent: November 4, 2014Assignee: United Technologies CorporationInventors: Seth J. Thomen, Christopher Corcoran
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Publication number: 20140165591Abstract: A gas turbine engine stage includes a rotor having a slot. A blade has a root received in the slot, and a shank that extends radially outward from the root to a platform that supports an airfoil. A seal is supported on the shank and in engagement circumferentially between and with the shank and the rotor within the slot. A gas turbine engine includes compressor and turbine sections. The turbine section has a rotor with a slot. A combustor is provided axially between the compressor and turbine sections. A turbine blade in the turbine section includes a root received in the slot and a shank that extends radially outward from the root to a platform that supports an airfoil.Type: ApplicationFiled: December 18, 2012Publication date: June 19, 2014Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Seth J. Thomen, Wieslaw A. Chlus
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Publication number: 20140112792Abstract: A damper pin for coupling platforms of adjacent turbine blades includes a first flat longitudinal end region, a second flat longitudinal end region and a reduced cross sectional area. The reduced cross sectional area is separated from the first flat longitudinal end region by a first main body region and the reduced cross sectional area is separated from the second flat longitudinal end region by a second main body region. The cross sectional area of the reduced cross sectional area is less than the cross sectional area of each of the first and second main body regions.Type: ApplicationFiled: December 30, 2013Publication date: April 24, 2014Applicant: United Technologies CorporationInventors: Seth J. Thomen, Christopher Corcoran