Patents by Inventor Sasha M. Moore
Sasha M. Moore 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: 10982552Abstract: A gas turbine engine component includes a wall that provides an exterior surface and an interior flow path surface. The wall has a wall thickness. A protrusion is arranged on the wall that extends a height beyond the wall thickness and provides a portion of the interior flow path surface. A film cooling hole that has an inlet is provided on the protrusion and extends to an exit on the exterior surface.Type: GrantFiled: August 21, 2015Date of Patent: April 20, 2021Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Sasha M. Moore, Clifford J. Musto, Timothy J. Jennings, Thomas N. Slavens, San Quach, Nicholas M LoRicco, John McBrien, Carey Clum, Christopher Whitfield
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Patent number: 10954800Abstract: One exemplary embodiment of this disclosure relates to a method of forming an engine component. The method includes forming an engine component having an internal passageway, the internal passageway formed with an initial dimension. The method further includes establishing a flow of machining fluid within the internal passageway, the machining fluid changing the initial dimension.Type: GrantFiled: August 10, 2018Date of Patent: March 23, 2021Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Sasha M. Moore, Thomas N. Slavens, Nicholas M. Loricco, Timothy J. Jennings
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Patent number: 10808546Abstract: An airfoil for a gas turbine engine includes an outer airfoil wall that provides an exterior surface and multiple radially extending cooling passages. The exterior surface provides pressure and suctions sides joined by leading and trailing edges. The cooling passages include a supply passage arranged upstream from and in fluid communication with a trailing edge passage. A cooling hole extends through the outer airfoil wall from the supply passage to the exterior surface on the suction side.Type: GrantFiled: March 27, 2019Date of Patent: October 20, 2020Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Sarah Riley, Sasha M. Moore, Jeffrey R. Levine
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Patent number: 10415394Abstract: A blade for a gas turbine engine includes an airfoil that extends a span from a root to a tip. The airfoil is provided by a first portion near the root and has a metallic alloy. A third portion near the tip has a refractory material. A second portion joins the first and third portions and has a functional graded material.Type: GrantFiled: December 2, 2014Date of Patent: September 17, 2019Assignee: United Technologies CorporationInventors: Thomas N. Slavens, Mosheshe Camara-Khary Blake, Timothy J. Jennings, Nicholas M. LoRicco, Sasha M. Moore, Clifford J. Musto
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Publication number: 20190218916Abstract: An airfoil for a gas turbine engine includes an outer airfoil wall that provides an exterior surface and multiple radially extending cooling passages. The exterior surface provides pressure and suctions sides joined by leading and trailing edges. The cooling passages include a supply passage arranged upstream from and in fluid communication with a trailing edge passage. A cooling hole extends through the outer airfoil wall from the supply passage to the exterior surface on the suction side.Type: ApplicationFiled: March 27, 2019Publication date: July 18, 2019Inventors: Sarah Riley, Sasha M. Moore, Jeffrey R. Levine
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Publication number: 20190176228Abstract: A gas turbine engine includes a structure that has walls that provide a cooling passage and a cooling surface. A non-ferrous obstruction is relative to the walls. The obstruction includes a portion spaced from the cooling surface to provide a gap which is configured to receive a cooling fluid.Type: ApplicationFiled: February 14, 2019Publication date: June 13, 2019Inventors: Thomas N. Slavens, Lane Thornton, Sasha M. Moore, Nicholas M. LoRicco
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Patent number: 10259039Abstract: A method of manufacturing a component that includes providing a core structure, casting a component about the core structure, removing a first portion of the core structure from the cast component, and leaving a second portion of the core structure in the cast component to provide a reduced cross-section in the cast component.Type: GrantFiled: January 16, 2014Date of Patent: April 16, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Thomas N. Slavens, Lane Thornton, Sasha M. Moore, Nicholas M. LoRicco
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Patent number: 10253634Abstract: An airfoil for a gas turbine engine includes an outer airfoil wall that provides an exterior surface and multiple radially extending cooling passages. The exterior surface provides pressure and suctions sides joined by leading and trailing edges. The cooling passages include a supply passage arranged upstream from and in fluid communication with a trailing edge passage. A cooling hole extends through the outer airfoil wall from the supply passage to the exterior surface on the suction side.Type: GrantFiled: April 25, 2014Date of Patent: April 9, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Sarah Riley, Sasha M. Moore, Jeffrey R. Levine
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Patent number: 10253635Abstract: A turbine blade according to an example of the present disclosure includes, among other things, a platform extending from a root section, an airfoil section extending radially from the platform to an airfoil tip, a plurality of cooling passages defined in an external wall of the airfoil tip, the plurality of cooling passages extending radially between the airfoil tip and a cavity in the airfoil section bounded by the external wall, and each of the plurality of cooling passages defining an inlet port along the cavity and an exit port adjacent the airfoil tip, and at least one internal feature within each of the plurality of cooling passages that meter flow to the respective exit port.Type: GrantFiled: April 30, 2018Date of Patent: April 9, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Dominic J. Mongillo, Jr., Jeffrey R. Levine, Kyle C. Lana, Sasha M. Moore
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Patent number: 10196902Abstract: A gas turbine engine component includes a body with a wall surrounding an interior cavity. The wall has opposed interior and exterior surfaces. The interior surface has a plurality of coolant inlets and the exterior surface has a coolant outlet defined therein. A coolant conduit extends between the coolant inlets and the coolant outlet and is configured and adapted to induce secondary flow vortices in coolant traversing the coolant conduit and in an adherent coolant film over a portion of the exterior surface of component body.Type: GrantFiled: September 15, 2015Date of Patent: February 5, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Sasha M. Moore, Timothy J. Jennings, Thomas N. Slavens, Clifford J. Musto, Nicholas M. LoRicco, Carey Clum, John McBrien, Christopher Whitfield, San Quach
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Publication number: 20180363473Abstract: One exemplary embodiment of this disclosure relates to a method of forming an engine component. The method includes forming an engine component having an internal passageway, the internal passageway formed with an initial dimension. The method further includes establishing a flow of machining fluid within the internal passageway, the machining fluid changing the initial dimension.Type: ApplicationFiled: August 10, 2018Publication date: December 20, 2018Inventors: Sasha M. Moore, Thomas N. Slavens, Nicholas M. Loricco, Timothy J. Jennings
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Patent number: 10107110Abstract: One exemplary embodiment of this disclosure relates to a method of forming an engine component. The method includes forming an engine component having an internal passageway, the internal passageway formed with an initial dimension. The method further includes establishing a flow of machining fluid within the internal passageway, the machining fluid changing the initial dimension.Type: GrantFiled: November 14, 2014Date of Patent: October 23, 2018Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Sasha M. Moore, Thomas N. Slavens, Nicholas M. Loricco, Timothy J. Jennings
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Publication number: 20180245470Abstract: A turbine blade according to an example of the present disclosure includes, among other things, a platform extending from a root section, an airfoil section extending radially from the platform to an airfoil tip, a plurality of cooling passages defined in an external wall of the airfoil tip, the plurality of cooling passages extending radially between the airfoil tip and a cavity in the airfoil section bounded by the external wall, and each of the plurality of cooling passages defining an inlet port along the cavity and an exit port adjacent the airfoil tip, and at least one internal feature within each of the plurality of cooling passages that meter flow to the respective exit port.Type: ApplicationFiled: April 30, 2018Publication date: August 30, 2018Inventors: Dominic J. Mongillo, JR., Jeffrey R. Levine, Kyle C. Lana, Sasha M. Moore
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Patent number: 10006371Abstract: A gas turbine engine component is described. The component includes a component wall having an internal surface that is adjacent a flow of coolant and an external surface that is adjacent a flow of gas. The component wall includes a cooling hole that has an inlet defined by the internal surface and an outlet defined by the external surface. The cooling holes also has a metering location having the smallest cross-section area of the cooling hole, an internal diffuser positioned between the inlet and the metering location, an accumulation diverter portion of the internal diffuser and an accumulator portion of the internal diffuser.Type: GrantFiled: August 14, 2015Date of Patent: June 26, 2018Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: John McBrien, Thomas N. Slavens, Clifford J. Musto, Timothy J. Jennings, Nicholas M. LoRicco, Sasha M. Moore
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Patent number: 9995147Abstract: A turbine blade according to an example of the present disclosure includes, among other things, a platform, an airfoil tip, and an airfoil section between the platform and the airfoil tip. The airfoil section has a cavity spaced radially from the airfoil tip and a plurality of cooling passages radially between the cavity and the airfoil tip. Each of the plurality of cooling passages defines an exit port adjacent the airfoil tip. An internal feature within each of the plurality of cooling passages is configured to meter flow to the exit port.Type: GrantFiled: February 11, 2015Date of Patent: June 12, 2018Assignee: United Technologies CorporationInventors: Dominic J. Mongillo, Jr., Jeffrey R. Levine, Kyle C. Lana, Sasha M. Moore
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Patent number: 9957810Abstract: A wall of a gas turbine engine is provided. The wall may comprise an external surface adjacent a gas path and an internal surface adjacent an internal flow path. A film hole may have an inlet at the internal surface and an outlet at the external surface. A flow accumulator adjacent the inlet may protrude from the internal surface. A method of making an engine component is also provided and comprises the step of forming a component wall comprising an accumulator on an internal surface and a film hole defined by the component wall. The film hole may include an opening adjacent the accumulator and defined by the internal surface.Type: GrantFiled: September 14, 2015Date of Patent: May 1, 2018Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Clifford J. Musto, Nicholas M. LoRicco, Thomas N. Slavens, Timothy J. Jennings, Carey Clum, Sasha M. Moore, John McBrien, San Quach, Christopher Whitfield
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Patent number: 9957814Abstract: A gas turbine engine component includes a wall that provides an exterior surface and an interior flow path surface. A film cooling hole extends through the wall and is configured to fluidly connect the interior flow path surface to the exterior surface. The film cooling hole has a pocket that faces the interior flow path and extends substantially in a longitudinal direction. The film cooling hole has a portion downstream from the pocket and is arranged at an angle relative to the longitudinal direction and extends to the exterior surface.Type: GrantFiled: August 17, 2015Date of Patent: May 1, 2018Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Clifford J. Musto, Sasha M. Moore, Thomas N. Slavens, San Quach, Nicholas M. LoRicco, Timothy J. Jennings, John McBrien
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Patent number: 9714580Abstract: This disclosure relates to a gas turbine engine including a first engine component and a second engine component. The first engine component has a mate face adjacent a mate face of the second engine component. The engine further includes a seal provided between the mate face of the first engine component and the mate face of the second engine component. The seal includes least one trough.Type: GrantFiled: July 24, 2014Date of Patent: July 25, 2017Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Thomas N. Slavens, Sasha M. Moore, Nicholas M. LoRicco
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Publication number: 20160312617Abstract: A blade for a gas turbine engine includes an airfoil that extends a span from a root to a tip. The airfoil is provided by a first portion near the root and has a metallic alloy. A third portion near the tip has a refractory material. A second portion joins the first and third portions and has a functional graded material.Type: ApplicationFiled: December 2, 2014Publication date: October 27, 2016Inventors: Thomas N. Slavens, Mosheshe Camara-Khary Blake, Timothy J. Jennings, Nicholas M. LoRicco, Sasha M. Moore, Clifford J. Musto
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Publication number: 20160258299Abstract: One exemplary embodiment of this disclosure relates to a method of forming an engine component. The method includes forming an engine component having an internal passageway, the internal passageway formed with an initial dimension. The method further includes establishing a flow of machining fluid within the internal passageway, the machining fluid changing the initial dimension.Type: ApplicationFiled: November 14, 2014Publication date: September 8, 2016Inventors: Sasha M. Moore, Thomas N. Slavens, Nicholas M. Loricco, Timothy J. Jennings