Patents by Inventor Justin D. Piggush
Justin D. Piggush 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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Publication number: 20120207616Abstract: The pattern has a pattern material and a casting core combination. The pattern material has an airfoil. The casting core combination is at least partially embedded in the pattern material. The casting core combination comprises a metallic casting core and at least one additional casting core. The metallic casting core has opposite first and second faces. The metallic core and at least one additional casting core extend spanwise into the airfoil of the pattern material. In at least a portion of the pattern material outside the airfoil of the pattern material, the metallic casting core is bent transverse to the spanwise direction so as to at least partially surround an adjacent portion of the at least one additional casting core.Type: ApplicationFiled: April 5, 2012Publication date: August 16, 2012Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Tracy A. Propheter-Hinckley, Justin D. Piggush, Yongxiang D. Xue, Amarnath Ramlogan, Anthony P. Cherolis, Matthew A. Devore, Eric P. Letizia
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Publication number: 20120141289Abstract: A turbine engine airfoil includes an airfoil structure having an exterior surface providing a leading edge. A radially extending first cooling passage is arranged near the leading edge and includes first and second portions. The first portion extends to the exterior surface and forms a radially extending trench in the leading edge. The second portion is in fluid communication with a second cooling passage. In one example, the second cooling passage extends radially, and the first cooling passage wraps around a portion of the second cooling passage from a pressure side to a suction side between the second cooling passage and the exterior surface. In the example, the first portion is arranged between the pressure and suction sides. In one example, the first cooling passage is formed by arranging a core in an airfoil mold. The trench is formed by the core in one example.Type: ApplicationFiled: February 6, 2012Publication date: June 7, 2012Inventors: William Abdel-Messeh, Justin D. Piggush
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Patent number: 8171978Abstract: The pattern has a pattern material and a casting core combination. The pattern material has an airfoil. The casting core combination is at least partially embedded in the pattern material. The casting core combination comprises a metallic casting core and at least one additional casting core. The metallic casting core has opposite first and second faces. The metallic core and at least one additional casting core extend spanwise into the airfoil of the pattern material. In at least a portion of the pattern material outside the airfoil of the pattern material, the metallic casting core is bent transverse to the spanwise direction so as to at least partially surround an adjacent portion of the at least one additional casting core.Type: GrantFiled: November 21, 2008Date of Patent: May 8, 2012Assignee: United Technologies CorporationInventors: Tracy A. Propheter-Hinckley, Justin D. Piggush, Yongxiang D. Xue, Amarnath Ramlogan, Anthony P. Cherolis, Matthew A. Devore, Eric P. Letizia
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Publication number: 20120101792Abstract: A method for developing a component includes establishing a performance requirement to predict the secondary crystallographic orientation for a component having orthogonal x, y, and z axes. The component is to be formed from a single crystal material having a primary crystallographic orientation along the z-axis and a secondary crystallographic orientation substantially in the x-y plane. A property of the component is computer simulated as a function of an angle of the secondary crystallographic orientation relative to the x-axis. Based on the computer simulation, the angle for the component is selected which will substantially satisfy the performance requirement.Type: ApplicationFiled: October 25, 2010Publication date: April 26, 2012Inventors: Alexander Staroselsky, Justin D. Piggush, Dominic J. Mongillo, JR.
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Patent number: 8157527Abstract: A turbine engine airfoil includes an airfoil structure having an exterior surface and an end portion. A cooling passage extends a length radially within the structure in a direction toward the end portion. The cooling passage provides a convection surface along the length adjacent to the exterior surface. The convection surface includes a generally uniform width along the length. The cooling passage has generally decreasing cross-sectional areas along the length in the direction.Type: GrantFiled: July 3, 2008Date of Patent: April 17, 2012Assignee: United Technologies CorporationInventors: Justin D. Piggush, William Abdel-Messeh
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Patent number: 8137068Abstract: The pattern has a pattern material and a casting core combination. The pattern material has an airfoil. The casting core combination is at least partially embedded in the pattern material. The casting core combination comprises a plurality of metallic casting cores. Each metallic casting core has opposite first and second faces and a respective portion along the trailing edge of the airfoil. At least two of the metallic cores have sections offset between the pressure side and the suction side.Type: GrantFiled: November 21, 2008Date of Patent: March 20, 2012Assignee: United Technologies CorporationInventors: Raymond Surace, Justin D. Piggush, Tracy A. Propheter-Hinckley, Amarnath Ramlogan, Yongxiang D. Xue, Anthony P. Cherolis, Matthew A. Devore, Eric P. Letizia
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Patent number: 8109725Abstract: A turbine engine airfoil includes an airfoil structure having an exterior surface providing a leading edge. A radially extending first cooling passage is arranged near the leading edge and includes first and second portions. The first portion extends to the exterior surface and forms a radially extending trench in the leading edge. The second portion is in fluid communication with a second cooling passage. In one example, the second cooling passage extends radially, and the first cooling passage wraps around a portion of the second cooling passage from a pressure side to a suction side between the second cooling passage and the exterior surface. In the example, the first portion is arranged between the pressure and suction sides. In one example, the first cooling passage is formed by arranging a core in an airfoil mold. The trench is formed by the core in one example.Type: GrantFiled: December 15, 2008Date of Patent: February 7, 2012Assignee: United Technologies CorporationInventors: William Abdel-Messeh, Justin D. Piggush
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Patent number: 8105030Abstract: Cooled airfoils and gas turbine engine systems involving such airfoils are provided. In this regard, a representative cooled airfoil includes: an exterior surface defining a leading edge, a trailing edge, a suction side and a pressure side; an interior surface defining an interior cavity; trenches in the exterior surface oriented spanwise along the leading edge; and cooling holes communicating between the interior cavity and the trenches such that cooling air provided to the interior cavity flows from the interior cavity though the cooling holes into the trenches, the cooling holes having exterior apertures located in the trenches and interior apertures located at the interior surface.Type: GrantFiled: August 14, 2008Date of Patent: January 31, 2012Assignee: United Technologies CorporationInventors: William Abdel-Messeh, Michael F. Blair, Atul Kohli, Justin D. Piggush
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Patent number: 8100165Abstract: An investment casting core combination includes a metallic casting core and a ceramic feedcore. A first region of the metallic casting core is embedded in the ceramic feedcore. A mating edge portion of the metallic casting core includes a number of projections. The first region is along at least some of the projections. A number of recesses span gaps between adjacent projections. The ceramic feedcore includes a number of compartments respectively receiving the metallic casting core projections. The ceramic feedcore further includes a number of portions between the compartments and respectively received in the metallic casting core recesses.Type: GrantFiled: November 17, 2008Date of Patent: January 24, 2012Assignee: United Technologies CorporationInventors: Justin D. Piggush, Karl A. Mentz, Richard H. Page, Jesse R. Christophel, Ricardo Trindade
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Publication number: 20110315337Abstract: A method involves forming a core assembly. The forming includes deforming a wire, the deforming including increasing a transverse linear dimension along at least one portion of the wire.Type: ApplicationFiled: September 1, 2011Publication date: December 29, 2011Applicant: UNITED TECHNOLOGIES CORPORATIONInventor: Justin D. Piggush
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Patent number: 7980820Abstract: A blade is provided for a turbine engine that includes an exterior surface. The exterior surface includes a portion having a thermal barrier coating and an uncoated shelf adjacent to the thermal barrier coating without the thermal barrier coating. A cooling hole extends from an internal passageway through the exterior surface to an exit. A scarfed channel is recessed in the exterior surface and interconnected to the cooling hole at the exit. The scarfed channel extends to a blade tip end surface. The scarfed channel protects the cooling fluid exiting the cooling hole from secondary flows surrounding the blade that would otherwise mix with and disperse the cooling fluid. The scarfed channels also increase the surface area exposed to the cooling fluid to increase the heat transfer rate.Type: GrantFiled: August 27, 2007Date of Patent: July 19, 2011Assignee: United Technologies CorporationInventors: Scott W. Gayman, Justin D. Piggush, Edward F. Pietraszkiewicz, William A. Agli, III
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Publication number: 20100150733Abstract: A turbine engine airfoil includes an airfoil structure having an exterior surface providing a leading edge. A radially extending first cooling passage is arranged near the leading edge and includes first and second portions. The first portion extends to the exterior surface and forms a radially extending trench in the leading edge. The second portion is in fluid communication with a second cooling passage. In one example, the second cooling passage extends radially, and the first cooling passage wraps around a portion of the second cooling passage from a pressure side to a suction side between the second cooling passage and the exterior surface. In the example, the first portion is arranged between the pressure and suction sides. In one example, the first cooling passage is formed by arranging a core in an airfoil mold. The trench is formed by the core in one example.Type: ApplicationFiled: December 15, 2008Publication date: June 17, 2010Inventors: William Abdel-Messeh, Justin D. Piggush
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Publication number: 20100129194Abstract: The pattern has a pattern material and a casting core combination. The pattern material has an airfoil. The casting core combination is at least partially embedded in the pattern material. The casting core combination comprises a metallic casting core and at least one additional casting core. The metallic casting core has opposite first and second faces. The metallic core and at least one additional casting core extend spanwise into the airfoil of the pattern material. In at least a portion of the pattern material outside the airfoil of the pattern material, the metallic casting core is bent transverse to the spanwise direction so as to at least partially surround an adjacent portion of the at least one additional casting core.Type: ApplicationFiled: November 21, 2008Publication date: May 27, 2010Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Tracy A. Propheter-Hinckley, Justin D. Piggush, Yongxiang D. Xue, Amarnath Ramlogan, Anthony P. Cherolis, Matthew A. Devore, Eric P. Letizia
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Publication number: 20100129195Abstract: The pattern has a pattern material and a casting core combination. The pattern material has an airfoil. The casting core combination is at least partially embedded in the pattern material. The casting core combination comprises a plurality of metallic casting cores. Each metallic casting core has opposite first and second faces and a respective portion along the trailing edge of the airfoil. At least two of the metallic cores have sections offset between the pressure side and the suction side.Type: ApplicationFiled: November 21, 2008Publication date: May 27, 2010Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Raymond Surace, Justin D. Piggush, Tracy A. Propheter-Hinckley, Amarnath Ramlogan, Yongxiang D. Xue, Anthony P. Cherolis, Matthew A. Devore, Eric P. Letizia
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Publication number: 20100122789Abstract: An investment casting core combination includes a metallic casting core and a ceramic feedcore. A first region of the metallic casting core is embedded in the ceramic feedcore. A mating edge portion of the metallic casting core includes a number of projections. The first region is along at least some of the projections. A number of recesses span gaps between adjacent projections. The ceramic feedcore includes a number of compartments respectively receiving the metallic casting core projections. The ceramic feedcore further includes a number of portions between the compartments and respectively received in the metallic casting core recesses.Type: ApplicationFiled: November 17, 2008Publication date: May 20, 2010Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Justin D. Piggush, Karl A. Mentz, Richard H. Page, Jesse R. Christophel, Ricardo Trindade
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Publication number: 20100098526Abstract: A turbine engine airfoil includes an airfoil structure having a side with an exterior surface. The structure includes a cooling passage extending a length within the structure and providing a convection surface facing the side. The convection surface is twisted along the length, which varies a heat transfer rate between the exterior surface and the convection surface along the length. In one example, the cooling passage is provided by a refractory metal core that is used during the airfoil casting process. The core includes multiple legs joined by a connecting portion. At least one of the legs is twisted along its length. The legs are deformed toward one another opposite the connecting portion to provide a desired core shape that corresponds to the shape of the cooling passage. Accordingly, the cooling passage provides desired cooling of the airfoil.Type: ApplicationFiled: October 16, 2008Publication date: April 22, 2010Inventor: Justin D. Piggush
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Publication number: 20100054953Abstract: A turbine engine airfoil includes an airfoil structure having an exterior surface that provides a leading edge. A first cooling passage includes radially spaced legs extending laterally from one side of the leading edge toward another side of the leading edge and interconnecting to form a loop with one another. A trench extends radially in the exterior surface along the leading edge. The trench intersects one of the first and second legs to provide at least one first cooling hole in the trench.Type: ApplicationFiled: August 29, 2008Publication date: March 4, 2010Inventor: Justin D. Piggush
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Publication number: 20100040478Abstract: Cooled airfoils and gas turbine engine systems involving such airfoils are provided. In this regard, a representative cooled airfoil includes: an exterior surface defining a leading edge, a trailing edge, a suction side and a pressure side; an interior surface defining an interior cavity; trenches in the exterior surface oriented spanwise along the leading edge; and cooling holes communicating between the interior cavity and the trenches such that cooling air provided to the interior cavity flows from the interior cavity though the cooling holes into the trenches, the cooling holes having exterior apertures located in the trenches and interior apertures located at the interior surface.Type: ApplicationFiled: August 14, 2008Publication date: February 18, 2010Applicant: UNITED TECHNOLOGIES CORP.Inventors: William Abdel-Messeh, Michael F. Blair, Atul Kohli, Justin D. Piggush
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Publication number: 20100003142Abstract: A turbine engine airfoil includes an airfoil structure having an exterior surface and an end portion. A cooling passage extends a length radially within the structure in a direction toward the end portion. The cooling passage provides a convection surface along the length adjacent to the exterior surface. The convection surface includes a generally uniform width along the length. The cooling passage has generally decreasing cross-sectional areas along the length in the direction.Type: ApplicationFiled: July 3, 2008Publication date: January 7, 2010Inventors: Justin D. Piggush, William Abdel-Messeh
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Publication number: 20090060741Abstract: A blade is provided for a turbine engine that includes an exterior surface. The exterior surface includes a portion having a thermal barrier coating and an uncoated shelf adjacent to the thermal barrier coating without the thermal barrier coating. A cooling hole extends from an internal passageway through the exterior surface to an exit. A scarfed channel is recessed in the exterior surface and interconnected to the cooling hole at the exit. The scarfed channel extends to a blade tip end surface. The scarfed channel protects the cooling fluid exiting the cooling hole from secondary flows surrounding the blade that would otherwise mix with and disperse the cooling fluid. The scarfed channels also increase the surface area exposed to the cooling fluid to increase the heat transfer rate.Type: ApplicationFiled: August 27, 2007Publication date: March 5, 2009Inventors: Scott W. Gayman, Justin D. Piggush, Edward F. Pietraszkiewicz, William A. Agli, III