Patents by Inventor EVAN ANDREW SEWALL
EVAN ANDREW SEWALL 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: 10989070Abstract: A turbine having a stationary shroud ring formed about rotor blades. The stationary shroud ring may include an inner shroud segment. The inner shroud segment may include a cooling configuration that includes a crossflow channel. The crossflow channel may extend lengthwise between an upstream end and a downstream end, and, therebetween, include a junction point that divides the crossflow channel lengthwise into upstream and downstream sections, with the upstream section extending between the upstream end and the junction point, and the downstream section extending between the junction point and the downstream end. The crossflow channel may have a cross-sectional flow area that varies lengthwise such that a cross-sectional flow area of the upstream section decreases between the upstream end and the junction point, and a cross-sectional flow area of the downstream section increases between the junction point and the downstream end.Type: GrantFiled: May 31, 2018Date of Patent: April 27, 2021Assignee: General Electric CompanyInventors: Brad Wilson VanTassel, Evan Andrew Sewall, Joseph Anthony Weber, Travis J Packer, Joseph Daniel Franzen, Jr., Bryan David Lewis
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Patent number: 10815807Abstract: A turbine of a gas turbine engine that includes a stationary shroud ring having inner shroud segments circumferentially stacked about a hot gas path. The inner shroud segments may include a first inner shroud segment that includes: a cooling configuration having cooling channels configured to receive and direct a coolant through an interior of the first inner shroud segment, where each of the cooling channels extends lengthwise between a first end and a second end that includes an outlet formed through an exterior surface of the first inner shroud segment; a circumferential edge; a slot formed in the circumferential edge; and a sealing member positioned within the slot. The outlet of at least one of the cooling channels may be positioned within the slot.Type: GrantFiled: May 31, 2018Date of Patent: October 27, 2020Assignee: General Electric CompanyInventors: Brad Wilson VanTassel, Steven Paul Byam, Joseph Anthony Weber, Evan Andrew Sewall, Travis J Packer
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Patent number: 10550710Abstract: A turbine shroud segment including: a target exterior surface and target interior region; and a cooling configuration having first and second channel types. The first channel type includes: an inlet and outlet; a target section extending through the target interior region; lateral ports spaced lengthwise between first and second ends of the target section; and a path within the target interior region offset from the target exterior surface by a minimum offset. The second channel type includes: dead-ends disposed at first and second ends; lateral ports connecting to lateral ports of the first channel type; and a path through the target interior region that is variable between valleys and peaks. The second channel type resides closer to the target exterior surface at the valleys than at the peaks. At each of the valleys, the second channel type resides within the minimum offset.Type: GrantFiled: May 31, 2018Date of Patent: February 4, 2020Assignee: GENERAL ELECTRIC COMPANYInventors: Brad Wilson VanTassel, Evan Andrew Sewall, Travis J Packer
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Publication number: 20190368377Abstract: A turbine having a stationary shroud ring formed about rotor blades. The stationary shroud ring may include an inner shroud segment. The inner shroud segment may include a cooling configuration that includes a crossflow channel. The crossflow channel may extend lengthwise between an upstream end and a downstream end, and, therebetween, include a junction point that divides the crossflow channel lengthwise into upstream and downstream sections, with the upstream section extending between the upstream end and the junction point, and the downstream section extending between the junction point and the downstream end. The crossflow channel may have a cross-sectional flow area that varies lengthwise such that a cross-sectional flow area of the upstream section decreases between the upstream end and the junction point, and a cross-sectional flow area of the downstream section increases between the junction point and the downstream end.Type: ApplicationFiled: May 31, 2018Publication date: December 5, 2019Applicant: General Electric CompanyInventors: Brad Wilson VanTassel, Evan Andrew Sewall, Joseph Anthony Weber, Travis J Packer, Joseph Daniel Franzen, JR., Bryan David Lewis
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Publication number: 20190368364Abstract: A turbine of a gas turbine engine that includes a stationary shroud ring having inner shroud segments circumferentially stacked about a hot gas path. The inner shroud segments may include a first inner shroud segment that includes: a cooling configuration having cooling channels configured to receive and direct a coolant through an interior of the first inner shroud segment, where each of the cooling channels extends lengthwise between a first end and a second end that includes an outlet formed through an exterior surface of the first inner shroud segment; a circumferential edge; a slot formed in the circumferential edge; and a sealing member positioned within the slot. The outlet of at least one of the cooling channels may be positioned within the slot.Type: ApplicationFiled: May 31, 2018Publication date: December 5, 2019Applicant: General Electric CompanyInventors: Brad Wilson VanTassel, Steven Paul Byam, Joseph Anthony Weber, Evan Andrew Sewall, Travis J. Packer
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Publication number: 20190368365Abstract: A turbine shroud segment including: a target exterior surface and target interior region; and a cooling configuration having first and second channel types. The first channel type includes: an inlet and outlet; a target section extending through the target interior region; lateral ports spaced lengthwise between first and second ends of the target section; and a path within the target interior region offset from the target exterior surface by a minimum offset. The second channel type includes: dead-ends disposed at first and second ends; lateral ports connecting to lateral ports of the first channel type; and a path through the target interior region that is variable between valleys and peaks. The second channel type resides closer to the target exterior surface at the valleys than at the peaks. At each of the valleys, the second channel type resides within the minimum offset.Type: ApplicationFiled: May 31, 2018Publication date: December 5, 2019Applicant: General Electric CompanyInventors: Brad Wilson VanTassel, Evan Andrew Sewall, Travis J. Packer
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Patent number: 9169733Abstract: A turbine airfoil assembly has an airfoil with an inner wall, an outer wall, a leading edge and a trailing edge. The airfoil has one or more chambers extending in a substantially chordwise direction of the airfoil. An insert has a plurality of impingement holes, and the insert is configured to be inserted within one of the chambers. The insert is configured to cool the airfoil via the plurality of impingement holes. A chambering element is attached only to the insert, the chambering element is configured to provide an increased cooling gas pressure inside a boundary area defined by the chambering element relative to an area outside the boundary area. A gap exists between the inner wall of the airfoil and the chambering element, and the gap allows cooling gas to exit the boundary area and enter the area outside the boundary area.Type: GrantFiled: March 20, 2013Date of Patent: October 27, 2015Assignee: General Electric CompanyInventors: Onika Misasha Kerber, Gary Michael Itzel, James William Vehr, Evan Andrew Sewall
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Publication number: 20140286762Abstract: A turbine airfoil assembly has an airfoil with an inner wall, an outer wall, a leading edge and a trailing edge. The airfoil has one or more chambers extending in a substantially chordwise direction of the airfoil. An insert has a plurality of impingement holes, and the insert is configured to be inserted within one of the chambers. The insert is configured to cool the airfoil via the plurality of impingement holes. A chambering element is attached only to the insert, the chambering element is configured to provide an increased cooling gas pressure inside a boundary area defined by the chambering element relative to an area outside the boundary area. A gap exists between the inner wall of the airfoil and the chambering element, and the gap allows cooling gas to exit the boundary area and enter the area outside the boundary area.Type: ApplicationFiled: March 20, 2013Publication date: September 25, 2014Applicant: General Electric CompanyInventors: Onika Misasha Kerber, Gary Michael Itzel, James William Vehr, Evan Andrew Sewall
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Patent number: 8651799Abstract: A turbine vane or blade segment includes at least one airfoil extending radially outwardly from a radially inner band. A plurality of cooling passages are formed in the radially inner band in fluid communication with an internal plenum in the airfoil and exiting the inner band via a plurality of exit holes in the one of the axially-extending side edges of the inner band. The plurality of exit holes are confined to a region along the one of the axially-extending side edges where static pressure PS along the one of the substantially axially-extending side edges lies in a pressure range substantially between the stage inlet total pressure PT and a pressure that is substantially about 1.5 times the dynamic pressure range ?PD, below the stage inlet total pressure.Type: GrantFiled: June 2, 2011Date of Patent: February 18, 2014Assignee: General Electric CompanyInventors: Evan Andrew Sewall, James William Vehr, Frederic Woodrow Roberts, Jr.
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Publication number: 20120308399Abstract: A turbine vane or blade segment includes at least one airfoil extending radially outwardly from a radially inner band. The radially inner band is formed with substantially axially-extending side edges, and the at least one airfoil is formed with a leading edge, a trailing edge, a pressure side, a suction side, and an internal cooling plenum. The pressure side faces one of the substantially axially-extending side edges and the leading edge is located proximate to that one edge. A plurality of cooling passages are formed in the radially inner band in fluid communication with the internal plenum and exiting the inner band via a plurality of exit holes in the one of the substantially axially-extending side edges.Type: ApplicationFiled: June 2, 2011Publication date: December 6, 2012Applicant: GENERAL ELECTRIC COMPANYInventors: Evan Andrew SEWALL, James William VEHR, Frederic Woodrow ROBERTS, JR.
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Publication number: 20100284800Abstract: A turbine nozzle segment includes an outer band portion, an inner band portion, and at least one nozzle vane extending between the band portions. A cooling plenum is defined in a mating side face of at least one of the band portions and extends transversely at least partially through the respective band portion. First and second cooling passages extend from the cooling plenum to respective first and second cooling chambers.Type: ApplicationFiled: May 11, 2009Publication date: November 11, 2010Applicant: GENERAL ELECTRIC COMPANYInventors: EVAN ANDREW SEWALL, DAVID RICHARD JOHNS, GARY MICHAEL ITZEL