Patents by Inventor Jason Edward Albert
Jason Edward Albert 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: 10830072Abstract: The present disclosure is directed to a turbomachine airfoil including an exterior wall having a trailing edge. The exterior wall defines a radially-extending cooling cavity and one or more trailing edge cooling passages extending through the exterior wall. Each trailing edge cooling passage includes an inlet in fluid communication with the cooling cavity and a first portion in fluid communication with the inlet. Each trailing edge cooling passage also includes a second portion in fluid communication with the first portion. The second portion includes a first outlet defined by the exterior wall at the trailing edge. Each trailing edge cooling passage further includes a third portion in fluid communication with the first portion. The third portion includes a second outlet defined by the exterior wall at the trailing edge. The second and third portions are separated by a rib extending upstream from the trailing edge.Type: GrantFiled: July 24, 2017Date of Patent: November 10, 2020Assignee: General Electric CompanyInventor: Jason Edward Albert
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Patent number: 10689994Abstract: Various embodiments include gas turbine seals and methods of forming such seals. In some cases, a turbine includes: a first arcuate component adjacent to a second arcuate component, each arcuate component including one or more slots located in an end face, each of the one or more slots having a plurality of axial surfaces and radially facing surfaces extending from opposite ends of the axial surfaces and a seal assembly disposed in the slot. The seal assembly including a backup intersegment seal disposed in the slot on a high-pressure side of the slot and a shim seal disposed in the slot over the backup intersegment seal and covering the backup intersegment seal on a low-pressure side of the slot. The shim seal including one or more shim seal segments and having a gap formed between each of the one or more shim seal segments.Type: GrantFiled: March 31, 2016Date of Patent: June 23, 2020Assignee: General Electric CompanyInventors: Jason Edward Albert, Bodhayan Dev, Neelesh Nandkumar Sarawate, Michael John Brown
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Patent number: 10267171Abstract: The present disclosure relates to a turbomachine that includes a first component and a second component coupled to another and a seal assembly disposed between the two components. The seal assembly may include an upstream corner shim, a downstream corner shim, and/or one or more intersegment seals that are configured to block a flow of fluid between the two components.Type: GrantFiled: December 8, 2015Date of Patent: April 23, 2019Assignee: General Electric CompanyInventors: Bodhayan Dev, Neelesh Nandkumar Sarawate, Jason Edward Albert
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Patent number: 10247024Abstract: The present disclosure relates to a turbomachine that includes a first component and a second component coupled to another and a seal assembly between the two components. The seal assembly may include an upstream corner shim and a downstream corner shim, where one of the upstream corner shim or the downstream corner shim includes a pressure actuation feature configured to block a flow of gas between the two components.Type: GrantFiled: December 8, 2015Date of Patent: April 2, 2019Assignee: GENERAL ELECTRIC COMPANYInventors: Bodhayan Dev, Neelesh Nandkumar Sarawate, Jason Edward Albert
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Publication number: 20190024519Abstract: The present disclosure is directed to a turbomachine airfoil including an exterior wall having a trailing edge. The exterior wall defines a radially-extending cooling cavity and one or more trailing edge cooling passages extending through the exterior wall. Each trailing edge cooling passage includes an inlet in fluid communication with the cooling cavity and a first portion in fluid communication with the inlet. Each trailing edge cooling passage also includes a second portion in fluid communication with the first portion. The second portion includes a first outlet defined by the exterior wall at the trailing edge. Each trailing edge cooling passage further includes a third portion in fluid communication with the first portion. The third portion includes a second outlet defined by the exterior wall at the trailing edge. The second and third portions are separated by a rib extending upstream from the trailing edge.Type: ApplicationFiled: July 24, 2017Publication date: January 24, 2019Inventor: Jason Edward Albert
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Patent number: 10132195Abstract: Cooling air extracted from a gas turbine engine compressor is sent to nozzle vane cooling passage inlets, through the cooling passages, and to purge tubes of a set of two or more vanes. A mixing chamber formed between the purge tubes in a diaphragm cavity receives fluid from the purge tubes and directs it through exit passage(s) formed through a wall of the mixing chamber to a surface of the diaphragm. The exit passage(s) can be inclined to induce a fluid velocity component substantially parallel to the surface and/or in a rotation direction of a turbine wheel.Type: GrantFiled: October 20, 2015Date of Patent: November 20, 2018Assignee: GENERAL ELECTRIC COMPANYInventors: Matthew Peter Scoffone, Jason Edward Albert, Michael Robert Berry, Mitchell Allan Merrill
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Patent number: 10125632Abstract: Cooling air extracted from a gas turbine engine compressor is sent to a nozzle vane cooling passage inlet, through the cooling passage, and to a purge tube of the vane. A mixing chamber formed in a diaphragm cavity receives fluid from the purge tube and directs it through exit passage(s) formed through a side wall of the mixing chamber and/or diaphragm cavity to a diametral surface of the diaphragm. The exit passage(s) can be inclined to induce a fluid velocity component substantially parallel to the diametral surface and/or in a rotation direction of a turbine wheel adjacent the diaphragm.Type: GrantFiled: October 20, 2015Date of Patent: November 13, 2018Assignee: General Electric CompanyInventors: Matthew Peter Scoffone, Jason Edward Albert, Michael Robert Berry, Mitchell Allan Merrill
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Patent number: 10094231Abstract: The present disclosure relates to a turbomachine that includes a first component and a second component coupled to another and a seal assembly between the two components. The seal assembly may include a first intersegment seal, a second intersegment seal, and a rope seal that are configured to block a flow of gas between the two components.Type: GrantFiled: December 8, 2015Date of Patent: October 9, 2018Assignee: General Electric CompanyInventors: Bodhayan Dev, Neelesh Nandkumar Sarawate, Jason Edward Albert, Christopher Edward Wolfe
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Patent number: 9970299Abstract: The present application provides a purge flow delivery system that may be used with a gas turbine engine. The purge flow delivery system may include a mixing chamber with a first sidewall, a second sidewall, and a cover plate, a first inlet tube positioned about the first sidewall, the first inlet tube configured to deliver a first fluid to the mixing chamber, a second inlet tube positioned about the second sidewall, the second inlet tube configured to deliver a second fluid to the mixing chamber, and a baffle plate attached to the cover plate and positioned to direct the first fluid at a first angle and the second fluid at a second angle.Type: GrantFiled: September 16, 2015Date of Patent: May 15, 2018Assignee: GENERAL ELECTRIC COMPANYInventors: Matthew Peter Scoffone, Jason Edward Albert, Mitchell Merrill
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Patent number: 9869194Abstract: Various embodiments include gas turbine seals and methods of forming such seals. In some cases, a turbine includes: a first arcuate component adjacent to a second arcuate component, each arcuate component including one or more slots located in an end face, each of the one or more slots having a plurality of axial surfaces and radially facing surfaces extending from opposite ends of the axial surfaces and a seal assembly disposed in the slot. The seal assembly including an intersegment seal including a plurality of seal segments defining one or more corner regions. The intersegment seal disposed in a slot defining a high-pressure slot side and a low-pressure slot side, wherein the slot includes a plurality of slot segments. Each of the plurality of seal segments including at least one extended portion to either seal the one or more corner regions on a low-pressure slot side, form a recess in the intersegment seal, or both.Type: GrantFiled: March 31, 2016Date of Patent: January 16, 2018Assignee: General Electric CompanyInventors: Bodhayan Dev, Robert Carl Meyer, Neelesh Nandkumar Sarawate, Jason Edward Albert, Gary Michael Itzel
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Publication number: 20170284214Abstract: Various embodiments include gas turbine seals and methods of forming such seals. In some cases, a turbine includes: a first arcuate component adjacent to a second arcuate component, each arcuate component including one or more slots located in an end face, each of the one or more slots having a plurality of axial surfaces and radially facing surfaces extending from opposite ends of the axial surfaces and a seal assembly disposed in the slot. The seal assembly including a backup intersegment seal disposed in the slot on a high-pressure side of the slot and a shim seal disposed in the slot over the backup intersegment seal and covering the backup intersegment seal on a low-pressure side of the slot. The shim seal including one or more shim seal segments and having a gap formed between each of the one or more shim seal segments.Type: ApplicationFiled: March 31, 2016Publication date: October 5, 2017Inventors: Jason Edward Albert, Bodhayan Dev, Neelesh Nandkumar Sarawate, Michael John Brown
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Publication number: 20170284215Abstract: Various embodiments include gas turbine seals and methods of forming such seals. In some cases, a turbine includes: a first arcuate component adjacent to a second arcuate component, each arcuate component including one or more slots located in an end face, each of the one or more slots having a plurality of axial surfaces and radially facing surfaces extending from opposite ends of the axial surfaces and a seal assembly disposed in the slot. The seal assembly including an intersegment seal including a plurality of seal segments defining one or more corner regions. The intersegment seal disposed in a slot defining a high-pressure slot side and a low-pressure slot side, wherein the slot includes a plurality of slot segments. Each of the plurality of seal segments including at least one extended portion to either seal the one or more corner regions on a low-pressure slot side, form a recess in the intersegment seal, or both.Type: ApplicationFiled: March 31, 2016Publication date: October 5, 2017Inventors: Bodhayan Dev, Robert Carl Meyer, Neelesh Nandkumar Sarawate, Jason Edward Albert, Gary Michael Itzel
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Publication number: 20170159479Abstract: The present disclosure relates to a turbomachine that includes a first component and a second component coupled to another and a seal assembly between the two components. The seal assembly may include an upstream corner shim and a downstream corner shim, where one of the upstream corner shim or the downstream corner shim includes a pressure actuation feature configured to block a flow of gas between the two components.Type: ApplicationFiled: December 8, 2015Publication date: June 8, 2017Inventors: Bodhayan Dev, Neelesh Nandkumar Sarawate, Jason Edward Albert
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Publication number: 20170159478Abstract: The present disclosure relates to a turbomachine that includes a first component and a second component coupled to another and a seal assembly disposed between the two components. The seal assembly may include an upstream corner shim, a downstream corner shim, and/or one or more intersegment seals that are configured to block a flow of fluid between the two components.Type: ApplicationFiled: December 8, 2015Publication date: June 8, 2017Inventors: Bodhayan Dev, Neelesh Nandkumar Sarawate, Jason Edward Albert
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Publication number: 20170159480Abstract: The present disclosure relates to a turbomachine that includes a first component and a second component coupled to another and a seal assembly between the two components. The seal assembly may include a first intersegment seal, a second intersegment seal, and a rope seal that are configured to block a flow of gas between the two components.Type: ApplicationFiled: December 8, 2015Publication date: June 8, 2017Inventors: Bodhayan Dev, Neelesh Nandkumar Sarawate, Jason Edward Albert, Christopher Edward Wolfe
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Publication number: 20170107850Abstract: Cooling air extracted from a gas turbine engine compressor is sent to a nozzle vane cooling passage inlet, through the cooling passage, and to a purge tube of the vane. A mixing chamber formed in a diaphragm cavity receives fluid from the purge tube and directs it through exit passage(s) formed through a side wall of the mixing chamber and/or diaphragm cavity to a diametral surface of the diaphragm. The exit passage(s) can be inclined to induce a fluid velocity component substantially parallel to the diametral surface and/or in a rotation direction of a turbine wheel adjacent the diaphragm.Type: ApplicationFiled: October 20, 2015Publication date: April 20, 2017Inventors: Matthew Peter Scoffone, Jason Edward Albert, Michael Robert Berry, Mitchell Allan Merrill
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Publication number: 20170107853Abstract: Cooling air extracted from a gas turbine engine compressor is sent to nozzle vane cooling passage inlets, through the cooling passages, and to purge tubes of a set of two or more vanes. A mixing chamber formed between the purge tubes in a diaphragm cavity receives fluid from the purge tubes and directs it through exit passage(s) formed through a wall of the mixing chamber to a surface of the diaphragm. The exit passage(s) can be inclined to induce a fluid velocity component substantially parallel to the surface and/or in a rotation direction of a turbine wheel.Type: ApplicationFiled: October 20, 2015Publication date: April 20, 2017Inventors: Matthew Peter Scoffone, Jason Edward Albert, Michael Robert Berry, Mitchell Allan Merrill
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Publication number: 20170074106Abstract: The present application provides a purge flow delivery system that may be used with a gas turbine engine. The purge flow delivery system may include a mixing chamber with a first sidewall, a second sidewall, and a cover plate, a first inlet tube positioned about the first sidewall, the first inlet tube configured to deliver a first fluid to the mixing chamber, a second inlet tube positioned about the second sidewall, the second inlet tube configured to deliver a second fluid to the mixing chamber, and a baffle plate attached to the cover plate and positioned to direct the first fluid at a first angle and the second fluid at a second angle.Type: ApplicationFiled: September 16, 2015Publication date: March 16, 2017Inventors: Matthew Peter Scoffone, Jason Edward Albert, Mitchell Merrill
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Publication number: 20160090843Abstract: Turbine components include at least one fluid flow passage at least one aperture disposed on a surface of the turbine component and fluidly connected to the at least one fluid flow passage. The at least one aperture includes a floor extending from the at least one fluid flow passage to the surface; and, a step disposed between an inner portion of the floor and an outer portion of the floor such that the inner portion of the floor and the outer portion of the floor do not comprise a single planar surface.Type: ApplicationFiled: September 30, 2014Publication date: March 31, 2016Inventors: Jason Edward Albert, Gary Michael Itzel, Steven Paul Byam, Jaime Javier Maldonado, Brian Gene Brzek, Thomas Robert Reid, Jonathan Matthew Lomas
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Patent number: 8955576Abstract: A core assembly for a turbine engine blade includes a generally radially extending trunk interconnected to multiple generally axially extending tabs. The tabs are interconnected by a generally radially extending ligament. Multiple generally axially extending protrusions are interconnected to the ligament opposite the trunk. A mold is configured to define an exterior surface of an airfoil. The core is arranged within the mold and is configured such that the tabs and the ligament break through at the exterior surface.Type: GrantFiled: January 15, 2014Date of Patent: February 17, 2015Assignee: United Technologies CorporationInventors: Jason Edward Albert, Atul Kohli, Eric L. Couch