Patents by Inventor Andrew P. Boursy
Andrew P. Boursy 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: 11098604Abstract: An engine component for a gas turbine engine may include a radial channel and an axial channel disposed in the engine component. The radial channel may be configured to direct a cooling air in a radial direction. The axial channel may be configured to direct the cooling air in a direction substantially perpendicular to the radial direction. A cross-section area of the axial channel is greater than a cross-section area of the radial channel, such that the radial channel remains the metering channel, independent of the relative location due to radial movement of the engine component with respect to an adjacent engine component.Type: GrantFiled: September 6, 2019Date of Patent: August 24, 2021Assignee: Raytheon Technologies CorporationInventor: Andrew P. Boursy
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Patent number: 11041396Abstract: An air seal may comprise an annular ring defined by at least a proximal surface, a distal surface, an aft side and a forward side. A channel may be disposed in the forward side of the air seal and/or the aft side of the air seal and may extend between the proximal surface and the distal surface. An additional channel extending from at least one of the forward side or the aft side may be disposed in the distal surface. The channel and the additional channel may be circumferentially in line. The channels may define a flow path for direction cooling air from a proximal side of the air seal to a distal side of the air seal. The radial channel may interface with the axial channel at an edge of the air seal.Type: GrantFiled: July 31, 2019Date of Patent: June 22, 2021Assignee: Raytheon Technologies CorporationInventors: James W Taubler, Peter E Gunderson, Sunny Anant Patel, Andrew P Boursy
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Publication number: 20200032666Abstract: An engine component for a gas turbine engine may include a radial channel and an axial channel disposed in the engine component. The radial channel may be configured to direct a cooling air in a radial direction. The axial channel may be configured to direct the cooling air in a direction substantially perpendicular to the radial direction. A cross-section area of the axial channel is greater than a cross-section area of the radial channel, such that the radial channel remains the metering channel, independent of the relative location due to radial movement of the engine component with respect to an adjacent engine component.Type: ApplicationFiled: September 6, 2019Publication date: January 30, 2020Applicant: UNITED TECHNOLOGIES CORPORATIONInventor: Andrew P. Boursy
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Publication number: 20190383155Abstract: An air seal may comprise an annular ring defined by at least a proximal surface, a distal surface, an aft side and a forward side. A channel may be disposed in the forward side of the air seal and/or the aft side of the air seal and may extend between the proximal surface and the distal surface. An additional channel extending from at least one of the forward side or the aft side may be disposed in the distal surface. The channel and the additional channel may be circumferentially in line. The channels may define a flow path for direction cooling air from a proximal side of the air seal to a distal side of the air seal. The radial channel may interface with the axial channel at an edge of the air seal.Type: ApplicationFiled: July 31, 2019Publication date: December 19, 2019Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: JAMES W. TAUBLER, Peter E. Gunderson, Sunny Anant Patel, Andrew P. Boursy
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Patent number: 10415410Abstract: An air seal may comprise an annular ring defined by at least a proximal surface, a distal surface, an aft side and a forward side. A channel may be disposed in the forward side of the air seal and/or the aft side of the air seal and may extend between the proximal surface and the distal surface. An additional channel extending from at least one of the forward side or the aft side may be disposed in the distal surface. The channel and the additional channel may be circumferentially in line. The channels may define a flow path for direction cooling air from a proximal side of the air seal to a distal side of the air seal.Type: GrantFiled: October 6, 2016Date of Patent: September 17, 2019Assignee: United Technologies CorporationInventors: James W Taubler, Peter E Gunderson, Sunny Anant Patel, Andrew P Boursy
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Patent number: 10047617Abstract: An airfoil component for a gas turbine engine includes a platform. The airfoil component includes a flow path surface from which an airfoil extends. A laterally extending aft surface is adjacent to the flow path surface. A contoured surface adjoins the flow path surface and the aft surface. An airfoil component for a gas turbine engine includes a platform. The airfoil component includes a flow path surface from which an airfoil extends. A laterally extending aft surface is adjacent to the flow path surface. A contoured surface adjoins the flow path surface and the aft surface. The aft surface extends from a first aft edge to a second aft edge at a circumferentially extending edge. The contoured surface is arranged inboard from at least one of the first and second edges.Type: GrantFiled: April 7, 2014Date of Patent: August 14, 2018Assignee: United Technologies CorporationInventors: Ky H. Vu, Lisa P. O'Neill, Takao Fukuda, Gerald M. Mace, Jr., Andy Turko, Andrew P. Boursy, Lynn M. Boy
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Patent number: 9945240Abstract: A power turbine section for a gas turbine engine includes a heat shield assembly mounted to a bearing support, the heat shield assembly forms an outer diameter directed toward an inner vane platform of the power turbine vane array.Type: GrantFiled: October 13, 2014Date of Patent: April 17, 2018Assignee: PW POWER SYSTEMS, INC.Inventors: Fernando K Grant, Fabian D. Betancourt, John J Korzendorfer, Andrew P Boursy, Alexander Sankovich, Henry K Webster, Christopher W Moore, Charles C Wu
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Publication number: 20180100404Abstract: An air seal may comprise an annular ring defined by at least a proximal surface, a distal surface, an aft side and a forward side. A channel may be disposed in the forward side of the air seal and/or the aft side of the air seal and may extend between the proximal surface and the distal surface. An additional channel extending from at least one of the forward side or the aft side may be disposed in the distal surface. The channel and the additional channel may be circumferentially in line. The channels may define a flow path for direction cooling air from a proximal side of the air seal to a distal side of the air seal.Type: ApplicationFiled: October 6, 2016Publication date: April 12, 2018Applicant: United Technologies CorporationInventors: James W. Taubler, Peter E. Gunderson, Sunny Anant Patel, Andrew P. Boursy
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Publication number: 20160102580Abstract: A power turbine section for a gas turbine engine includes an inlet duct upstream of a first power turbine vane array, the inlet duct including a lip.Type: ApplicationFiled: October 13, 2014Publication date: April 14, 2016Inventors: Fabian D. Betancourt, Fernando K. Grant, Andrew P. Boursy, Alexander Sankovich, Charles C. Wu
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Publication number: 20160102568Abstract: A power turbine section for a gas turbine engine includes a heat shield assembly mounted to a bearing support, the heat shield assembly forms an outer diameter directed toward an inner vane platform of the power turbine vane array.Type: ApplicationFiled: October 13, 2014Publication date: April 14, 2016Inventors: Fernando K. Grant, Fabian D. Betancourt, John J. Korzendorfer, Andrew P. Boursy, Alexander Sankovich, Henry K. Webster, Christopher W. Moore, Charles C. Wu
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Publication number: 20160053621Abstract: An airfoil component for a gas turbine engine includes a platform. The airfoil component includes a flow path surface from which an airfoil extends. A laterally extending aft surface is adjacent to the flow path surface. A contoured surface adjoins the flow path surface and the aft surface. An airfoil component for a gas turbine engine includes a platform. The airfoil component includes a flow path surface from which an airfoil extends. A laterally extending aft surface is adjacent to the flow path surface. A contoured surface adjoins the flow path surface and the aft surface. The aft surface extends from a first aft edge to a second aft edge at a circumferentially extending edge. The contoured surface is arranged inboard from at least one of the first and second edges.Type: ApplicationFiled: April 7, 2014Publication date: February 25, 2016Inventors: Ky H. Vu, Lisa P. O'Neill, Takao Fukuda, Gerald M. Mace, Jr., Andy Turko, Andrew P. Boursy, Lynn M. Boy
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Patent number: 6019575Abstract: A turbine (18) of a gas turbine engine includes erosion energy dissipaters (44) which comprise of a plurality of inlet orifices (46) and a large diameter outlet orifice (48). The erosion energy dissipater reduces erosion of associated structure due to impingement of particulates entrained in airstreams. Various construction details are described to provide cooling air containing entrained particulates to the high pressure turbine case of a gas turbine engine without eroding the case.Type: GrantFiled: September 12, 1997Date of Patent: February 1, 2000Assignee: United Technologies CorporationInventor: Andrew P. Boursy
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Patent number: 5415526Abstract: A rotor assembly 10 having a rotor disk 12 and a plurality of outwardly extending rotor blades 16 is disclosed. Various construction details are developed to provide effective cooling to the platform sections 20 of such rotor blades. In one particular embodiment, a damper 58 engages the underside of the rotor blades 16 and a seal member 42 inwardly of the damper engages the damper to provide damping of vibrations in the rotor blades. Both the damper and the seal member are provided with cooling air holes 42, 74 to positively distribute cooling air collected inwardly of the damper and seal member and to direct the cooling air preferentially between the adjacent platform sections 20 of the rotor blades to effectively cool the rotor blades.Type: GrantFiled: November 19, 1993Date of Patent: May 16, 1995Inventors: Anthony J. Mercadante, Andrews P. Boursy