Patents by Inventor Okey Kwon
Okey Kwon 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: 10196904Abstract: An airfoil may include a spar comprising a passageway inside of the spar for a cooling fluid, a pedestal on an outer surface of the spar, and an inlet configured to direct the cooling fluid from the passageway to the outer surface of the spar. The airfoil may further include a coversheet, wherein an inner surface of the coversheet is positioned on the pedestal of the spar and an edge of the coversheet is positioned along an end of the spar. The inner surface of the coversheet, the pedestal, and the outer surface of the spar may define a cooling path from the inlet to an outlet at the edge of the coversheet. The outlet at the edge of the coversheet may be configured to direct cooling fluid onto the end of the spar, onto a footing, and/or onto a fillet positioned along an intersection of the footing and the spar.Type: GrantFiled: January 24, 2016Date of Patent: February 5, 2019Assignees: ROLLS-ROYCE NORTH AMERICAN TECHNOLOGIES INC., ROLLS-ROYCE CORPORATIONInventors: Tab M. Heffernan, Jeffrey F. Rhodes, Douglas D. Dierksmeier, Okey Kwon
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Patent number: 10190418Abstract: One embodiment of the present invention is a unique turbine blade for a gas turbine engine. Another embodiment is a unique gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and turbine blades for gas turbine engines. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.Type: GrantFiled: December 28, 2012Date of Patent: January 29, 2019Assignee: Rolls-Royce North American Technologies Inc.Inventor: Okey Kwon
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Patent number: 9982541Abstract: A gas turbine engine flow path member is disclosed which includes an extending end portion capable of contacting a surface of the turbine engine. The flow path member includes openings to pass a cooling fluid to cool the extending end portion. The flow path member, furthermore, can be made using a variety of approaches. To set forth just two non-limiting examples, the flow path member can be cast and it can be a laminated construction.Type: GrantFiled: June 5, 2015Date of Patent: May 29, 2018Assignee: Rolls-Royce North American Technologies Inc.Inventors: Okey Kwon, Jeffrey F. Rhodes
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Patent number: 9915151Abstract: An airfoil may be provided that includes a CMC body and a support piece. The CMC body has an inner surface that defines a chamber within the CMC body. The support piece may be positioned within the chamber of the CMC body. The support piece comprises a channel in a surface of the support piece, the surface being in contact with the inner surface of the CMC body. The channel and the inner surface of the CMC body define a passageway for a cooling fluid. The passageway may wind about the circumference of the CMC body and extend along the span of the airfoil. Outlets may be positioned through the CMC body allowing fluid communication between the passageway and the outer surface of the CMC body.Type: GrantFiled: May 26, 2015Date of Patent: March 13, 2018Assignee: Rolls-Royce CorporationInventors: John Alan Weaver, Okey Kwon
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Patent number: 9879601Abstract: A gas turbine engine component is provided that can be cooled with a cooling media such as air using a variety of passages. In one form, cooling fluid is routed through a hole that exits at least partially through a pedestal formed between walls. A plurality of cooling holes can be provided through a trench face and in some forms can include a diffusion through a divergence in the hole exit. J-Hook passages can be provided through a trench face, and, in some forms, multiple trenches can be provided. A cooling hole having a neck portion can be provided, as can a cooling hole with one or more turns to reduce a total pressure. In one form, a corrugated cooling passage can be provided.Type: GrantFiled: December 31, 2013Date of Patent: January 30, 2018Assignee: Rolls-Royce North American Technologies Inc.Inventors: Peter C. Vandervaart, Jeffrey F. Rhodes, Okey Kwon, Tab M. Heffernan, Brett J. Barker
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Patent number: 9874110Abstract: A gas turbine component having a cooling passage is disclosed. In one form, the passage is oriented as a turned passage capable of reversing direction of flow, such as a turned cooling hole. The gas turbine engine component can include a layered structure having cooling flow throughout a region of the component. The cooling hole can be in communication with a space in the layered structure. The gas turbine engine component can be a cast article where a mold can be constructed to produce the cooling hole having a turn.Type: GrantFiled: December 27, 2013Date of Patent: January 23, 2018Assignee: Rolls-Royce North American Technologies Inc.Inventors: Peter C. Vandervaart, Jeffrey F. Rhodes, Okey Kwon, Tab M. Heffernan
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Publication number: 20170211395Abstract: An airfoil may include a spar comprising a passageway inside of the spar for a cooling fluid, a pedestal on an outer surface of the spar, and an inlet configured to direct the cooling fluid from the passageway to the outer surface of the spar. The airfoil may further include a coversheet, wherein an inner surface of the coversheet is positioned on the pedestal of the spar and an edge of the coversheet is positioned along an end of the spar. The inner surface of the coversheet, the pedestal, and the outer surface of the spar may define a cooling path from the inlet to an outlet at the edge of the coversheet. The outlet at the edge of the coversheet may be configured to direct cooling fluid onto the end of the spar, onto a footing, and/or onto a fillet positioned along an intersection of the footing and the spar.Type: ApplicationFiled: January 24, 2016Publication date: July 27, 2017Inventors: TAB M. HEFFERNAN, JEFFREY F. RHODES, DOUGLAS D. DIERKSMEIER, OKEY KWON
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Patent number: 9638057Abstract: An apparatus and method for cooling a dual, walled component is disclosed herein. An augmented cooling system according to the present disclosure includes transporting a cooling fluid through one wall of a cooling pathway formed between two opposing spaced apart walls of the dual walled component. The cooling fluid can be deflected away from one wall of the cooling pathway with a first trip strip as the cooling fluid traverses along the cooling pathway. The cooling fluid can be deflected away from the opposing wall of the cooling pathway with a second trip strip as the cooling fluid continues traversing along the cooling pathway. The cooling fluid can then be discharged from the cooling pathway through the opposing wall of the dual walled component.Type: GrantFiled: December 31, 2013Date of Patent: May 2, 2017Assignee: Rolls-Royce North American Technologies, Inc.Inventor: Okey Kwon
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Publication number: 20160348513Abstract: An airfoil may be provided that includes a CMC body and a support piece. The CMC body has an inner surface that defines a chamber within the CMC body. The support piece may be positioned within the chamber of the CMC body. The support piece comprises a channel in a surface of the support piece, the surface being in contact with the inner surface of the CMC body. The channel and the inner surface of the CMC body define a passageway for a cooling fluid. The passageway may wind about the circumference of the CMC body and extend along the span of the airfoil. Outlets may be positioned through the CMC body allowing fluid communication between the passageway and the outer surface of the CMC body.Type: ApplicationFiled: May 26, 2015Publication date: December 1, 2016Inventors: John Alan Weaver, Okey Kwon
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Publication number: 20160153284Abstract: A gas turbine engine flow path member is disclosed which includes an extending end portion capable of contacting a surface of the turbine engine. The flow path member includes openings to pass a cooling fluid to cool the extending end portion. The flow path member, furthermore, can be made using a variety of approaches. To set forth just two non-limiting examples, the flow path member can be cast and it can be a laminated construction.Type: ApplicationFiled: June 5, 2015Publication date: June 2, 2016Inventors: Okey Kwon, Jeffrey F. Rhodes
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Publication number: 20150300257Abstract: A gas turbine engine component is provided that can be cooled with a cooling media such as air using a variety of passages. In one form, cooling fluid is routed through a hole that exits at least partially through a pedestal formed between walls. A plurality of cooling holes can be provided through a trench face and in some forms can include a diffusion through a divergence in the hole exit. J-Hook passages can be provided through a trench face, and, in some forms, multiple trenches can be provided. A cooling hole having a neck portion can be provided, as can a cooling hole with one or more turns to reduce a total pressure. In one form, a corrugated cooling passage can be provided.Type: ApplicationFiled: December 31, 2013Publication date: October 22, 2015Inventors: Peter L. Vandervaart, Jeffrey F. Rhodes, Okey Kwon, Tab M. Heffernan, Brett J. Barker
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Patent number: 9085988Abstract: A gas turbine engine flow path member is disclosed which includes an extending end portion capable of contacting a surface of the turbine engine. The flow path member includes openings to pass a cooling fluid to cool the extending end portion. The flow path member, furthermore, can be made using a variety of approaches. To set forth just two non-limiting examples, the flow path member can be cast and it can be a laminated construction.Type: GrantFiled: December 22, 2011Date of Patent: July 21, 2015Assignee: Rolls-Royce North American Technologies, Inc.Inventors: Okey Kwon, Jeffrey F. Rhodes
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Patent number: 8961133Abstract: An cooled airfoil for a gas turbine engine is disclosed. The airfoil includes an outer wall having a plurality cooling air exit openings and an inner wall having plurality of cooling air inlet openings. A plurality of flow migration dams extend between the inner wall and the outer wall to form a plurality of cooling passages and prevent cooling air from moving radially outward past the migration dams.Type: GrantFiled: June 10, 2011Date of Patent: February 24, 2015Assignee: Rolls-Royce North American Technologies, Inc.Inventor: Okey Kwon
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Publication number: 20150016944Abstract: A gas turbine component having a cooling passage is disclosed. In one form, the passage is oriented as a turned passage capable of reversing direction of flow, such as a turned cooling hole. The gas turbine engine component can include a layered structure having cooling flow throughout a region of the component. The cooling hole can be in communication with a space in the layered structure. The gas turbine engine component can be a cast article where a mold can be constructed to produce the cooling hole having a turn.Type: ApplicationFiled: December 27, 2013Publication date: January 15, 2015Inventors: Peter L. Vandervaart, Jeffrey F. Rhodes, Okey Kwon, Tab M. Heffernan
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Publication number: 20150016947Abstract: An apparatus and method for cooling a dual, walled component is disclosed herein. An augmented cooling system according to the present disclosure includes transporting a cooling fluid through one wall of a cooling pathway formed between two opposing spaced apart walls of the dual walled component. The cooling fluid can be deflected away from one wall of the cooling pathway with a first trip strip as the cooling fluid traverses along the cooling pathway. The cooling fluid can be deflected away from the opposing wall of the cooling pathway with a second trip strip as the cooling fluid continues traversing along the cooling pathway. The cooling fluid can then be discharged from the cooling pathway through the opposing wall of the dual walled component.Type: ApplicationFiled: December 31, 2013Publication date: January 15, 2015Inventor: Okey Kwon
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Publication number: 20140311164Abstract: One embodiment of the present invention is a unique turbine blade for a gas turbine engine. Another embodiment is a unique gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and turbine blades for gas turbine engines. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.Type: ApplicationFiled: December 28, 2012Publication date: October 23, 2014Applicant: ROLLS-ROYCE NORTH AMERICAN TECHNOLOGIES, INC.Inventor: Okey Kwon
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Patent number: 8342797Abstract: In one embodiment, a gas turbine engine turbine flow member is described that contains a passageway having a flow obstruction that forms a tortuous passageway for the passage of a cooling fluid. The flow obstruction can include flow structures disposed toward either side of the passageway. In one non-limiting embodiment a flow structure can have a V-shape, and in another non-limiting embodiment the flow structure can have an elongate shape. As cooling fluid flows through the passageway it is encouraged to flow up, down, and/or along portions of the flow obstruction.Type: GrantFiled: August 31, 2009Date of Patent: January 1, 2013Assignee: Rolls-Royce North American Technologies Inc.Inventors: Okey Kwon, Ted Freeman
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Publication number: 20120189427Abstract: A gas turbine engine flow path member is disclosed which includes an extending end portion capable of contacting a surface of the turbine engine. The flow path member includes openings to pass a cooling fluid to cool the extending end portion. The flow path member, furthermore, can be made using a variety of approaches. To set forth just two non-limiting examples, the flow path member can be cast and it can be a laminated construction.Type: ApplicationFiled: December 22, 2011Publication date: July 26, 2012Inventors: Okey Kwon, Jeffrey F. Rhodes
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Publication number: 20120163994Abstract: One embodiment of the present invention is a unique gas turbine engine. Another embodiment is a unique turbine engine airfoil. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and airfoils. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.Type: ApplicationFiled: June 10, 2011Publication date: June 28, 2012Inventor: Okey Kwon
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Publication number: 20110052413Abstract: In one embodiment, a gas turbine engine turbine flow member is described that contains a passageway having a flow obstruction that forms a tortuous passageway for the passage of a cooling fluid. The flow obstruction can include flow structures disposed toward either side of the passageway. In one non-limiting embodiment a flow structure can have a V-shape, and in another non-limiting embodiment the flow structure can have an elongate shape. As cooling fluid flows through the passageway it is encouraged to flow up, down, and/or along portions of the flow obstruction.Type: ApplicationFiled: August 31, 2009Publication date: March 3, 2011Inventors: Okey Kwon, Ted Freeman