Patents by Inventor Shawn J. Gregg
Shawn J. Gregg 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: 11377965Abstract: A component for a gas turbine engine includes, among other things, an airfoil that extends between a leading edge and a trailing edge and a cooling circuit disposed inside of the airfoil. The cooling circuit includes at least one core cavity that extends inside of the airfoil, a baffle received within the at least one core cavity, a plurality of pedestals positioned adjacent to the at least one core cavity and a first plurality of axial ribs positioned between the plurality of pedestals and the trailing edge of the airfoil.Type: GrantFiled: March 6, 2017Date of Patent: July 5, 2022Assignee: Raytheon Technologies CorporationInventors: Shawn J. Gregg, Dominic J. Mongillo, Michael Leslie Clyde Papple, Russell J. Bergman, Mohammed Ennacer
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Patent number: 10502075Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a platform having a first path side and a second path side and a platform cooling circuit disposed on one of the first path side and the second path side of the platform. The platform cooling circuit includes a first core cavity, a cavity in fluid communication with the first core cavity, and a cover plate positioned to cover at least the cavity.Type: GrantFiled: November 24, 2015Date of Patent: December 10, 2019Assignee: United Technologies CorporationInventors: Michael Leslie Clyde Papple, Russell J. Bergman, Mohammed Ennacer, Shawn J. Gregg, Dominic J. Mongillo
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Patent number: 10239156Abstract: A method of forming a metal component having different regions containing different grain sizes and in porosities is by additive manufacturing. The method includes spreading a layer of starting powder on a temperature controlled moveable platform in a heated chamber with atmosphere and temperature control. Selected areas of the powder are melted and solidified with a computer controlled focused energy beam. The cooled platform is then indexed down and the process repeated. The grain size of the melted and solidified region can be controlled by the cooling rate during solidification which, in turn is controlled by the temperature of the chamber and the temperature of the cooled moveable platform.Type: GrantFiled: September 25, 2014Date of Patent: March 26, 2019Assignee: United Technologies CorporationInventors: Shawn J. Gregg, Alexander Staroselsky, Gajawalli V. Srinivasan
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Patent number: 10196917Abstract: A blade outer air seal for a gas turbine engine includes a wall, a forward hook, and an aft hook. The wall extends between the forward hook and the aft hook, which are adapted to mount the blade outer air seal to a casing of the gas turbine engine. The wall includes a cored passage extending along at least a portion of the wall. The cored passage extends radially and axially through a portion of the aft hook to communicate with one or more apertures along a trailing edge of the aft hook.Type: GrantFiled: July 1, 2015Date of Patent: February 5, 2019Assignee: United Technologies CorporationInventors: Paul M. Lutjen, Shawn J. Gregg, Thurman Carlo Dabbs, Ken F. Blaney, Russell E. Keene, Bruce E. Chick
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Patent number: 10024172Abstract: An airfoil includes an airfoil wall including an exterior airfoil surface and at least partially defines an airfoil cavity. A fillet is on the exterior airfoil surface. A recess is in an interior surface of the airfoil wall adjacent the fillet. A baffle tube is located in the airfoil cavity spaced from the recess.Type: GrantFiled: February 27, 2015Date of Patent: July 17, 2018Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Mark A. Boeke, Richard M. Salzillo, Jeffrey J. DeGray, Shawn J. Gregg
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Patent number: 9759072Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure including, among other things, an airfoil that extends between a leading edge and a trailing edge and a cooling circuit disposed inside of the airfoil. The cooling circuit includes at least one core cavity that extends inside of the airfoil, a baffle received within the at least one core cavity, a plurality of pedestals positioned adjacent to the at least one core cavity and a first plurality of axial ribs positioned between the plurality of pedestals and the trailing edge of the airfoil.Type: GrantFiled: August 30, 2012Date of Patent: September 12, 2017Assignee: United Technologies CorporationInventors: Shawn J. Gregg, Dominic J. Mongillo, Michael Leslie Clyde Papple, Russell J. Bergman, Mohammed Ennacer
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Publication number: 20170175631Abstract: A component for a gas turbine engine includes, among other things, an airfoil that extends between a leading edge and a trailing edge and a cooling circuit disposed inside of the airfoil. The cooling circuit includes at least one core cavity that extends inside of the airfoil, a baffle received within the at least one core cavity, a plurality of pedestals positioned adjacent to the at least one core cavity and a first plurality of axial ribs positioned between the plurality of pedestals and the trailing edge of the airfoil.Type: ApplicationFiled: March 6, 2017Publication date: June 22, 2017Inventors: Shawn J. Gregg, Dominic J. Mongillo, Michael Leslie Clyde Papple, Russell J. Bergman, Mohammed Ennacer
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Patent number: 9476313Abstract: According to an example embodiment, a gas turbine engine assembly includes, among other things, a compressor. A strut near the compressor includes a flow passage through a portion of the strut. The flow passage is configured to direct air from the compressor to another portion of the gas turbine engine. The flow passage has at least one surface feature that at least partially hinders some airflow through the flow passage.Type: GrantFiled: December 21, 2012Date of Patent: October 25, 2016Assignee: United Technologies CorporationInventors: Joseph T. Caprario, Shawn J. Gregg, Dave J. Hyland
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Publication number: 20160251969Abstract: An airfoil includes an airfoil wall including an exterior airfoil surface and at least partially defines an airfoil cavity. A fillet is on the exterior airfoil surface. A recess is in an interior surface of the airfoil wall adjacent the fillet. A baffle tube is located in the airfoil cavity spaced from the recess.Type: ApplicationFiled: February 27, 2015Publication date: September 1, 2016Inventors: Mark A. Boeke, Richard M. Salzillo, Jeffrey J. DeGray, Shawn J. Gregg
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Publication number: 20160214211Abstract: A method of forming a metal component having different regions containing different grain sizes and in porosities is by additive manufacturing. The method includes spreading a layer of starting powder on a temperature controlled moveable platform in a heated chamber with atmosphere and temperature control. Selected areas of the powder are melted and solidified with a computer controlled focused energy beam. The cooled platform is then indexed down and the process repeated. The grain size of the melted and solidified region can be controlled by the cooling rate during solidification which, in turn is controlled by the temperature of the chamber and the temperature of the cooled moveable platform.Type: ApplicationFiled: September 25, 2014Publication date: July 28, 2016Inventors: Shawn J. Gregg, Alexander Staroselsky, Gajawalli V. Srinivasan
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Patent number: 9334755Abstract: An airfoil component for a gas turbine engine includes an airfoil extending from a platform. At least one of the airfoil and the platform includes a cooling passage defined by a surface. A chevron-shaped trip strip extends from the surface into the cooling passage at a trip strip height along a length. The trip strip height varies along the length. A turbine vane for a gas turbine engine includes inner and outer platforms. A cooling passage is provided in the inner platform. The cooling passage is provided by first and second radially extending legs spaced circumferentially apart from one another and joined to one another by a circumferential passage. A pair of airfoils extend radially from the same inner platform. A trip strip extends from the surface into the circumferential passage at a trip strip height along a length. The trip strip height varying along the length.Type: GrantFiled: September 28, 2012Date of Patent: May 10, 2016Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Sarah Riley, Mark A. Boeke, Jeffrey J. DeGray, Shawn J. Gregg
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Publication number: 20160115803Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a platform having a first path side and a second path side and a platform cooling circuit disposed on one of the first path side and the second path side of the platform. The platform cooling circuit includes a first core cavity, a cavity in fluid communication with the first core cavity, and a cover plate positioned to cover at least the cavity.Type: ApplicationFiled: November 24, 2015Publication date: April 28, 2016Inventors: Michael Leslie Clyde PAPPLE, Russell J. BERGMAN, Mohammed ENNACER, Shawn J. GREGG, Dominic J. MONGILLO
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Publication number: 20160003152Abstract: A stator for a gas turbine engine has a platform supporting multiple vanes that includes first and second vanes respectively. First and second regions are arranged at the same location on the first and second vanes. The first and second regions respectively include first and second cooling hole configurations that are different than one another.Type: ApplicationFiled: March 12, 2014Publication date: January 7, 2016Inventors: Sarah Riley, Mark A. Boeke, Shawn J. Gregg
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Patent number: 9222364Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a platform having a first path side and a second path side and a platform cooling circuit disposed on one of the first path side and the second path side of the platform. The platform cooling circuit includes a first core cavity, a cavity in fluid communication with the first core cavity, and a cover plate positioned to cover at least the cavity.Type: GrantFiled: August 15, 2012Date of Patent: December 29, 2015Assignee: United Technologies CorporationInventors: Michael Leslie Clyde Papple, Russell J. Bergman, Mohammed Ennacer, Shawn J. Gregg, Dominic J. Mongillo
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Publication number: 20150300195Abstract: A blade outer air seal for a gas turbine engine includes a wall, a forward hook, and an aft hook. The wall extends between the forward hook and the aft hook, which are adapted to mount the blade outer air seal to a casing of the gas turbine engine. The wall includes a cored passage extending along at least a portion of the wall. The cored passage extends radially and axially through a portion of the aft hook to communicate with one or more apertures along a trailing edge of the aft hook.Type: ApplicationFiled: July 1, 2015Publication date: October 22, 2015Applicant: United Technologies CorporationInventors: Paul M. Lutjen, Shawn J. Gregg, Thurman Carlo Dabbs, Ken F. Blaney, Russell E. Keene, Bruce E. Chick
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Patent number: 9145775Abstract: An airfoil comprises pressure and suction surfaces extending axially from a leading edge to a trailing edge and radially from a root section to a tip section, the root section and the tip section defining a span therebetween. A thermal coating extends from the root section of the airfoil toward the tip section of the airfoil. A relative coating thickness of the thermal coating decreases by at least thirty percent at full span in the tip section, as compared to minimum span in the root section.Type: GrantFiled: March 2, 2012Date of Patent: September 29, 2015Assignee: United Technologies CorporationInventors: Jeffrey R. Levine, Shawn J. Gregg
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Patent number: 9103225Abstract: A blade outer air seal for a gas turbine engine includes a wall, a forward hook, and an aft hook. The wall extends between the forward hook and the aft hook, which are adapted to mount the blade outer air seal to a casing of the gas turbine engine. The wall includes a cored passage extending along at least a portion of the wall. The cored passage extends radially and axially through a portion of the aft hook to communicate with one or more apertures along a trailing edge of the aft hook.Type: GrantFiled: June 4, 2012Date of Patent: August 11, 2015Assignee: United Technologies CorporationInventors: Paul M. Lutjen, Shawn J. Gregg, Thurman Carlo Dabbs, Ken F. Blaney, Russell E. Keene, Bruce E. Chick
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Patent number: 9080452Abstract: A stator vane for a gas turbine engine includes an airfoil extending in a radial direction and supported by a platform having a gas flowpath surface. A cooling passage is arranged in the platform and includes a circumferential passage that is fluidly connected to an inlet passage extending through and edge of the platform, and film cooling holes extending from the gas flowpath surface to the circumferential passage, radial extending passage through the edge of the platform. A void is interconnected to at least one of the radially extending passage and the inlet passage.Type: GrantFiled: September 28, 2012Date of Patent: July 14, 2015Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Mark A. Boeke, Shawn J. Gregg, Sarah Riley, Jeffrey J. DeGray, Richard M. Salzillo
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Patent number: 8961108Abstract: A cooling system for a gas turbine engine includes a first plenum, a first cooling flow passageway, and a second cooling flow passageway. The first cooling flow passageway is in fluid communication with the first plenum and with a first airfoil cooling channel within an airfoil of the stator vane. The first airfoil cooling channel is for cooling a leading edge of the airfoil. The second cooling flow passageway is in fluid communication with the first plenum and with a platform cooling channel within an outer diameter platform of the stator vane. The first cooling flow passageway and the second cooling flow passageway are disposed within a mounting hook. The first cooling flow passageway and the second cooling flow passageway are not in fluid communication with each other.Type: GrantFiled: April 4, 2012Date of Patent: February 24, 2015Assignee: United Technologies CorporationInventors: Russell J. Bergman, Shawn J. Gregg, Michael Papple, Paul M. Lutjen, Joseph T. Caprario, Mohammed Ennacer, Thurman Carlo Dabbs
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Patent number: 8807955Abstract: An airfoil comprises a substrate, a residual abrasive coating and a supplemental abrasive coating. The substrate extends along a tip section of the airfoil, from a leading edge to a trailing edge. The residual abrasive coating comprises a two-phase abrasive and metal matrix material bonded to the substrate, on the tip section of the airfoil. The supplemental abrasive coating comprises a two-phase abrasive and metal matrix material bonded to the residual abrasive coating and to the substrate adjacent the residual abrasive coating, on the tip section of the airfoil. The supplemental abrasive coating restores the airfoil to a nominal tip height in the tip section.Type: GrantFiled: August 23, 2011Date of Patent: August 19, 2014Assignee: United Technologies CorporationInventors: Peter Wrabel, Peter J. Draghi, Shawn J. Gregg, Timothy P. Murphy