Patents by Inventor Kevin Richard Kirtley
Kevin Richard Kirtley 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: 10648346Abstract: A turbine rotor blade that includes a tip shroud attached to the outboard tip of the airfoil. The tip shroud may include an axially and circumferentially extending planar component in which an inboard surface opposes an outboard surface, and a shroud edge that connects the inboard surface to the outboard surface and defines an outboard profile of the tip shroud. The tip shroud may include a seal rail protruding from the outboard surface of the tip shroud and a cutter tooth disposed on the seal rail. The cutter tooth may be formed as a circumferential section of the seal rail that is axially thickened. The seal rail may further include a leakage gap formed therethrough that is configured to increase a leakage level during operation.Type: GrantFiled: July 6, 2016Date of Patent: May 12, 2020Assignee: General Electric CompanyInventors: Xiuzhang James Zhang, Kevin Richard Kirtley, Lisa DeBellis
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Publication number: 20180010467Abstract: A turbine rotor blade that includes a tip shroud attached to the outboard tip of the airfoil. The tip shroud may include an axially and circumferentially extending planar component in which an inboard surface opposes an outboard surface, and a shroud edge that connects the inboard surface to the outboard surface and defines an outboard profile of the tip shroud. The tip shroud may include a seal rail protruding from the outboard surface of the tip shroud and a cutter tooth disposed on the seal rail. The cutter tooth may be formed as a circumferential section of the seal rail that is axially thickened. The seal rail may further include a leakage gap formed therethrough that is configured to increase a leakage level during operation.Type: ApplicationFiled: July 6, 2016Publication date: January 11, 2018Applicant: General Electric CompanyInventors: Xiuzhang James Zhang, Kevin Richard Kirtley, Lisa DeBellis
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Patent number: 9863323Abstract: The present application and the resultant patent provide improved gas turbine component sealing. In one example embodiment, a gas turbine segment seal assembly may include a first tapered segment seal with a first tapered portion having a first tapered surface and a first taper angle. The gas turbine segment seal assembly may include a second tapered segment seal with a second tapered portion having a second tapered surface and a second taper angle. The gas turbine segment seal assembly may include a seal pin positioned in between the first tapered segment seal and the second segment seal and adjacent to the first tapered surface and the second tapered surface.Type: GrantFiled: February 17, 2015Date of Patent: January 9, 2018Assignee: GENERAL ELECTRIC COMPANYInventors: Kevin Richard Kirtley, Victor John Morgan
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Patent number: 9816388Abstract: A seal in a gas turbine engine includes a shim base and a honeycomb structure having a number of cavities are formed as a single unitary structure using additive manufacturing.Type: GrantFiled: September 22, 2016Date of Patent: November 14, 2017Assignee: General Electric CompanyInventors: Kevin Richard Kirtley, Ibrahim Sezer, Benjamin P. Lacy
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Patent number: 9771820Abstract: A turbine in a gas turbine engine that includes a stator blade and a rotor blade having a seal formed in a trench cavity. The trench cavity may include an axial gap defined between opposing inboard faces of the stator blade and rotor blade. The seal may include: a stator overhang extending from the stator blade toward the rotor blade so to include an outboard edge and an inboard edge and, defined therebetween, an overhang face; a rotor outboard face extending radially inboard from a platform edge, the rotor outboard face opposing at least a portion of the overhang face across the axial gap of the trench cavity; and a first axial projection extending from the rotor outboard face toward the stator blade. The stator overhang and the first axial projection of the rotor blade may be configured so to axially overlap.Type: GrantFiled: December 30, 2014Date of Patent: September 26, 2017Assignee: General Electric CompanyInventors: Richard William Johnson, Kevin Richard Kirtley, David Richard Johns, James William Vehr, Andrew Paul Giametta
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Patent number: 9765699Abstract: A gas turbine engine having a turbine that includes a stator blade and a rotor blade having a seal formed in a trench cavity defined therebetween. The seal may include: a stator overhang extending from the stator blade toward the rotor blade so to include an overhang topside, and, opposite the overhang topside, an overhang underside; a rotor outboard face extending radially inboard from a platform edge, the rotor outboard face opposing at least a portion of the overhang face across the axial gap of the trench cavity; an axial projection extending from the rotor outboard face toward the stator blade so to axially overlap with the stator overhang; and an interior cooling channel extending through the stator overhang to a port formed through the overhang underside. The port may be configured to direct a coolant expelled therefrom toward the axial projection.Type: GrantFiled: December 30, 2014Date of Patent: September 19, 2017Assignee: General Electric CompanyInventors: Kevin Richard Kirtley, David Richard Johns, Andrew Paul Giametta, Richard William Johnson
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Patent number: 9670785Abstract: A cooling assembly for a gas turbine system includes a turbine nozzle having at least one channel comprising a channel inlet configured to receive a cooling flow from a cooling source, wherein the at least one channel directs the cooling flow through the turbine nozzle in a radial direction at a first pressure to a channel outlet. Also included is an exit cavity for fluidly connecting the channel outlet to a region of a turbine component, wherein the region of the turbine component is at a second pressure, wherein the first pressure is greater than the second pressure.Type: GrantFiled: April 19, 2012Date of Patent: June 6, 2017Assignee: General Electric CompanyInventors: David Richard Johns, Kevin Richard Kirtley
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Publication number: 20160237912Abstract: The present application and the resultant patent provide improved gas turbine component sealing. In one example embodiment, a gas turbine segment seal assembly may include a first tapered segment seal with a first tapered portion having a first tapered surface and a first taper angle. The gas turbine segment seal assembly may include a second tapered segment seal with a second tapered portion having a second tapered surface and a second taper angle. The gas turbine segment seal assembly may include a seal pin positioned in between the first tapered segment seal and the second segment seal and adjacent to the first tapered surface and the second tapered surface.Type: ApplicationFiled: February 17, 2015Publication date: August 18, 2016Inventors: Kevin Richard Kirtley, Victor John Morgan
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Publication number: 20160186664Abstract: A gas turbine engine having a turbine that includes a stator blade and a rotor blade having a seal formed in a trench cavity defined therebetween. The seal may include: a stator overhang extending from the stator blade toward the rotor blade so to include an overhang topside, and, opposite the overhang topside, an overhang underside; a rotor outboard face extending radially inboard from a platform edge, the rotor outboard face opposing at least a portion of the overhang face across the axial gap of the trench cavity; an axial projection extending from the rotor outboard face toward the stator blade so to axially overlap with the stator overhang; and an interior cooling channel extending through the stator overhang to a port formed through the overhang underside. The port may be configured to direct a coolant expelled therefrom toward the axial projection.Type: ApplicationFiled: December 30, 2014Publication date: June 30, 2016Inventors: Kevin Richard Kirtley, David Richard Johns, Andrew Paul Giametta, Richard William Johnson
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Publication number: 20160186665Abstract: A turbine in a gas turbine engine that includes a stator blade and a rotor blade having a seal formed in a trench cavity. The trench cavity may include an axial gap defined between opposing inboard faces of the stator blade and rotor blade. The seal may include: a stator overhang extending from the stator blade toward the rotor blade so to include an outboard edge and an inboard edge and, defined therebetween, an overhang face; a rotor outboard face extending radially inboard from a platform edge, the rotor outboard face opposing at least a portion of the overhang face across the axial gap of the trench cavity; and a first axial projection extending from the rotor outboard face toward the stator blade. The stator overhang and the first axial projection of the rotor blade may be configured so to axially overlap.Type: ApplicationFiled: December 30, 2014Publication date: June 30, 2016Inventors: Richard William Johnson, Kevin Richard Kirtley, David Richard Johns, James William Vehr, Andrew Paul Giametta
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Patent number: 9334803Abstract: A method of recovering heat energy from a cooling medium used to cool hot gas path components in a turbine engine includes cooling one or more hot gas path components with the cooling medium; supplying spent cooling medium used to cool the one or more hot gas path components to a heat exchanger; supplying air (e.g., compressor discharge air) to the heat exchanger so as to be in heat exchange relationship with the spent cooling medium and thereby add heat to the compressor discharge air; and supplying the air heated in the heat exchanger to at least one combustor.Type: GrantFiled: August 20, 2013Date of Patent: May 10, 2016Assignee: General Electric CompanyInventors: John Charles Intile, Kevin Richard Kirtley
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Publication number: 20150052897Abstract: A method of recovering heat energy from a cooling medium used to cool hot gas path components in a turbine engine includes cooling one or more hot gas path components with the cooling medium; supplying spent cooling medium used to cool the one or more hot gas path components to a heat exchanger; supplying air (e.g., compressor discharge air) to the heat exchanger so as to be in heat exchange relationship with the spent cooling medium and thereby add heat to the compressor discharge air; and supplying the air heated in the heat exchanger to at least one combustor.Type: ApplicationFiled: August 20, 2013Publication date: February 26, 2015Applicant: General Electric CompanyInventors: John Charles INTILE, Kevin Richard KIRTLEY
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Patent number: 8961111Abstract: According to one aspect of the invention, a turbine airfoil includes a first cavity inside the turbine airfoil configured to receive a fluid and a second cavity inside the turbine airfoil. The turbine airfoil also includes a passage inside the turbine airfoil that provides fluid communication between the first and second cavities, wherein the passage includes a curved portion configured to separate particulates from the fluid as the fluid flows through the passage.Type: GrantFiled: January 3, 2012Date of Patent: February 24, 2015Assignee: General Electric CompanyInventors: Adebukola Oluwaseun Benson, Gary Michael Itzel, Kevin Richard Kirtley
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Publication number: 20150041590Abstract: An airfoil includes a main portion formed of a base material and having an inner core comprising a hollow region. Also included is a trailing edge region of the main portion. Further included is a trailing edge supplement structure comprising a low-melt superalloy operatively coupled to the base material proximate the trailing edge region. Yet further included is at least one cooling passage fluidly coupling the inner core of the main portion to an inner region of the trailing edge region. Also included is a trailing edge region exhaust path disposed in the inner region and configured to route a cooling airflow in a span-wise direction of the airfoil.Type: ApplicationFiled: August 9, 2013Publication date: February 12, 2015Applicant: General Electric CompanyInventors: Kevin Richard Kirtley, David Edward Schick, Aaron Ezekiel Smith
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Publication number: 20140154062Abstract: A seal for placement in a slot between two turbine components of a gas turbine to seal a gap between the components may include a sealing element sized so as to be capable of placement within the slot and of substantially sealing the gap during operation of the gas turbine. A sacrificial coating may be located on the sealing element. The sacrificial coating may be configured with a size substantially conforming to a size of the slot, the sacrificial coating including a material that is removable from the sealing element via heating to a temperature achieved during operation of the gas turbine. Related gas turbine assemblies and methods of assembly are also disclosed.Type: ApplicationFiled: November 30, 2012Publication date: June 5, 2014Applicant: GENERAL ELECTRIC COMPANYInventors: David Wayne Weber, Kevin Richard Kirtley, Victor John Morgan, Neelesh Nandkumar Sarawate
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Publication number: 20140116660Abstract: A method of fabricating a component is provided. The component includes a substrate having an outer surface and an inner surface, where the inner surface defines at least one interior space. The fabrication method includes forming at least one groove in the outer substrate surface. Each groove extends at least partially along the outer substrate surface and has an asymmetric cross-section. The method further includes forming at least one access hole in the substrate. Each access hole connects the respective groove in fluid communication with the respective interior space. A coating is disposed over at least a portion of the substrate surface, such that the groove(s) and the coating together define one or more channels for cooling the component. A component is also disclose and has at least one groove with an asymmetric cross-section.Type: ApplicationFiled: October 31, 2012Publication date: May 1, 2014Applicant: GENERAL ELECTRIC COMPANYInventors: Jesse Blair Butler, Ronald Scott Bunker, Scott Andrew Weaver, Kevin Richard Kirtley
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Publication number: 20140064325Abstract: A method of measuring local temperature variations at an interface between hot combustion gases in a turbine hot gas path and cooler purge air in a turbine rotor wheelspace includes applying a pressure- or temperature-sensitive paint to a rotatable turbine component where the hot combustion gas interacts with the purge air; locating at least one illumination device and at least one image-detecting device on a stationary component located proximate to the pressure sensitive paint; and, during operation of the turbine, imaging color changes in the pressure sensitive paint caused by local variations in partial pressure of oxygen which changes with temperature.Type: ApplicationFiled: September 6, 2012Publication date: March 6, 2014Applicant: General Electric CompanyInventor: Kevin Richard KIRTLEY
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Publication number: 20130280040Abstract: A cooling assembly for a gas turbine system includes a turbine nozzle having at least one channel comprising a channel inlet configured to receive a cooling flow from a cooling source, wherein the at least one channel directs the cooling flow through the turbine nozzle in a radial direction at a first pressure to a channel outlet. Also included is an exit cavity for fluidly connecting the channel outlet to a region of a turbine component, wherein the region of the turbine component is at a second pressure, wherein the first pressure is greater than the second pressure.Type: ApplicationFiled: April 19, 2012Publication date: October 24, 2013Applicant: GENERAL ELECTRIC COMPANYInventors: David Richard Johns, Kevin Richard Kirtley
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Publication number: 20130170982Abstract: According to one aspect of the invention, a turbine airfoil includes a first cavity inside the turbine airfoil configured to receive a fluid and a second cavity inside the turbine airfoil. The turbine airfoil also includes a passage inside the turbine airfoil that provides fluid communication between the first and second cavities, wherein the passage includes a curved portion configured to separate particulates from the fluid as the fluid flows through the passage.Type: ApplicationFiled: January 3, 2012Publication date: July 4, 2013Applicant: GENERAL ELECTRIC COMPANYInventors: Adebukola Oluwaseun Benson, Gary Michael Itzel, Kevin Richard Kirtley
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Patent number: 8393872Abstract: An airfoil is provided and includes a pressure surface and a suction surface. Radially corresponding surface characteristics of the pressure and suction surfaces at a spanwise local portion of the airfoil are formed to cooperatively define at least one of a camber line and a thickness distribution plot of the airfoil as having a radius of curvature with at least two sign changes. The number of sign changes decreases along a radial dimension of the airfoil measured from the spanwise local portion.Type: GrantFiled: October 23, 2009Date of Patent: March 12, 2013Assignee: General Electric CompanyInventor: Kevin Richard Kirtley