Patents by Inventor Sean D. Bradshaw
Sean D. Bradshaw 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: 11954042Abstract: Systems, methods and apparatuses of distributed computing based on memory as a service are described. For example, a set of networked computing devices can each be configured to execute an application that accesses memory using a virtual memory address region. Each respective device can map the virtual memory address region to the local memory for a first period of time during which the application is being executed in the respective device, map the virtual memory address region to a local memory of a remote device in the group for a second period of time after starting the application in the respective device and before terminating the application in the respective device, and request the remote device to process data in the virtual memory address region during at least the second period of time.Type: GrantFiled: September 13, 2022Date of Patent: April 9, 2024Assignee: Micron Technology, Inc.Inventors: Ameen D. Akel, Samuel E. Bradshaw, Kenneth Marion Curewitz, Sean Stephen Eilert, Dmitri Yudanov
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Patent number: 11041391Abstract: A gas turbine engine includes a combustor. A turbine section is in fluid communication with the combustor. The turbine section includes a first vane stage aft of the combustor. A plurality of vane cooling passages extending through a forward flange of the first vane stage to the radial inner surface for communicating cooling airflow into the core flow path forward of the leading edge. A seal assembly is disposed between the combustor and the forward flange of the vane stage. The seal includes a plurality of circumferentially spaced apart slots and a plurality of seal cooling passages that extend from the radially outer surface to the radially inner surface at each of the plurality of circumferentially spaced apart slots.Type: GrantFiled: April 20, 2020Date of Patent: June 22, 2021Assignee: Raytheon Technologies CorporationInventors: Steven D. Porter, Shawn M. McMahon, Kevin Zacchera, Noah Wadsworth, Christopher Whitfield, Sean D. Bradshaw, Dennis M. Moura, David Bitzko, Alex J. Schneider
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Patent number: 11015464Abstract: A gas turbine engine includes a combustor. A turbine section is in fluid communication with the combustor. The turbine section includes a first vane stage aft of the combustor. A seal assembly is disposed between the combustor and the first vane stage. The seal assembly includes a first plurality of openings and the first vane stage includes a second plurality of openings communicating cooling airflow into a gap between an aft end of the combustor and the first vane stage. A first vane stage assembly and a method are also disclosed.Type: GrantFiled: January 24, 2020Date of Patent: May 25, 2021Assignee: Raytheon Technologies CorporationInventors: Steven D. Porter, Shawn M. McMahon, Kevin Zacchera, Noah Wadsworth, Christopher Whitfield, Sean D. Bradshaw, Dennis M. Moura
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Publication number: 20200386106Abstract: A gas turbine engine includes a combustor. A turbine section is in fluid communication with the combustor. The turbine section includes a first vane stage aft of the combustor. A plurality of vane cooling passages extending through a forward flange of the first vane stage to the radial inner surface for communicating cooling airflow into the core flow path forward of the leading edge. A seal assembly is disposed between the combustor and the forward flange of the vane stage. The seal includes a plurality of circumferentially spaced apart slots and a plurality of seal cooling passages that extend from the radially outer surface to the radially inner surface at each of the plurality of circumferentially spaced apart slots.Type: ApplicationFiled: April 20, 2020Publication date: December 10, 2020Inventors: Steven D. Porter, Shawn M. McMahon, Kevin Zacchera, Noah Wadsworth, Christopher Whitfield, Sean D. Bradshaw, Dennis M. Moura, David Bitzko, Alex J. Schneider
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Publication number: 20200277867Abstract: A gas turbine engine includes a combustor. A turbine section is in fluid communication with the combustor. The turbine section includes a first vane stage aft of the combustor. A seal assembly is disposed between the combustor and the first vane stage. The seal assembly includes a first plurality of openings and the first vane stage includes a second plurality of openings communicating cooling airflow into a gap between an aft end of the combustor and the first vane stage. A first vane stage assembly and a method are also disclosed.Type: ApplicationFiled: January 24, 2020Publication date: September 3, 2020Inventors: Steven D. Porter, Shawn M. McMahon, Kevin Zacchera, Noah Wadsworth, Christopher Whitfield, Sean D. Bradshaw, Dennis M. Moura
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Patent number: 10738701Abstract: A gas turbine engine includes a combustor. A turbine section is in fluid communication with the combustor. The turbine section includes a first vane stage aft of the combustor. A seal assembly is disposed between the combustor and the first vane stage. The seal assembly includes a plurality of openings communicating cooling airflow into a gap between an aft end of the combustor and the first vane stage. A combustor assembly and method are also disclosed.Type: GrantFiled: August 30, 2017Date of Patent: August 11, 2020Assignee: Raytheon Technologies CorporationInventors: Steven D. Porter, Shawn M. McMahon, Kevin Zacchera, Noah Wadsworth, Christopher Whitfield, Sean D. Bradshaw, Dennis M. Moura
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Patent number: 10584601Abstract: A gas turbine engine includes a combustor. A turbine section is in fluid communication with the combustor. The turbine section includes a first vane stage aft of the combustor. A seal assembly is disposed between the combustor and the first vane stage. The seal assembly includes a first plurality of openings and the first vane stage includes a second plurality of openings communicating cooling airflow into a gap between an aft end of the combustor and the first vane stage. A first vane stage assembly and a method are also disclosed.Type: GrantFiled: August 30, 2017Date of Patent: March 10, 2020Assignee: United Technologies CorporationInventors: Steven D. Porter, Shawn M. McMahon, Kevin Zacchera, Noah Wadsworth, Christopher Whitfield, Sean D. Bradshaw, Dennis M. Moura
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Patent number: 10400672Abstract: A cooling system for a fuel injector system of a gas turbine engine has a heat exchanger for cooling a portion of diffuser case air and then routing the cooled diffuser case air through a sleeve that surrounds a fuel injector conduit located in at least the diffuser case plenum for minimizing fuel heat-up rates in the conduit. By minimizing fuel temperatures within the injector conduit, coking accumulation is thereby eliminated or reduced.Type: GrantFiled: October 31, 2014Date of Patent: September 3, 2019Assignee: United Technologies CorporationInventors: John D. Frish, Alexander W. Williams, Sean D. Bradshaw
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Patent number: 10260750Abstract: A combustor of a gas turbine engine including a combustor shell having an interior surface defining a combustion chamber, a first panel mounted to the interior surface at a first position, the first panel having a first surface and a first rail extending from the first surface toward the combustor shell, the first rail configured at a first angle relative to the first surface, and a second panel mounted to the interior surface at a second position axially adjacent to the first panel, the second panel having a second surface and a second rail extending from the second surface toward the combustor shell, the second rail configured at a second angle relative to the second surface. The first and second rails are proximal to each other and define a circumferential gap there between and at least one of the first or second angles is an acute angle.Type: GrantFiled: December 29, 2015Date of Patent: April 16, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: John S. Tu, James B. Hoke, Jonathan Jeffery Eastwood, Kevin Joseph Low, Sean D. Bradshaw
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Publication number: 20190063239Abstract: A gas turbine engine includes a combustor. A turbine section is in fluid communication with the combustor. The turbine section includes a first vane stage aft of the combustor. A seal assembly is disposed between the combustor and the first vane stage. The seal assembly includes a first plurality of openings and the first vane stage includes a second plurality of openings communicating cooling airflow into a gap between an aft end of the combustor and the first vane stage. A first vane stage assembly and a method are also disclosed.Type: ApplicationFiled: August 30, 2017Publication date: February 28, 2019Inventors: Steven D. Porter, Shawn M. McMahon, Kevin Zacchera, Noah Wadsworth, Christopher Whitfield, Sean D. Bradshaw, Dennis M. Moura
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Publication number: 20190063323Abstract: A gas turbine engine includes a combustor. A turbine section is in fluid communication with the combustor. The turbine section includes a first vane stage aft of the combustor. A seal assembly is disposed between the combustor and the first vane stage. The seal assembly includes a plurality of openings communicating cooling airflow into a gap between an aft end of the combustor and the first vane stage. A combustor assembly and method are also disclosed.Type: ApplicationFiled: August 30, 2017Publication date: February 28, 2019Inventors: Steven D. Porter, Shawn M. McMahon, Kevin Zacchera, Noah Wadsworth, Christopher Whitfield, Sean D. Bradshaw, Dennis M. Moura
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Patent number: 10060268Abstract: A turbine blade includes a platform that has a platform leading edge and trailing edge joined by two platform circumferential sides. An airfoil extends radially outwardly from the platform to a free tip end. The airfoil includes an airfoil leading edge and trailing edge joined by opposed pressure and suction sides. A root extends radially inwardly from the platform. The platform and the airfoil include film cooling holes that have external breakout points that are located in substantial conformance with the Cartesian coordinates set forth in Table 1. The Cartesian coordinates provided by an axial coordinate, a circumferential coordinate, and a radial coordinate, relative to a zero-coordinate, and the cooling holes have a diametrical surface tolerance relative to the specified coordinates of 0.200 inches (5.0 mm).Type: GrantFiled: December 10, 2015Date of Patent: August 28, 2018Assignee: UNITED TECHNOLOGIES CORPORATIONInventor: Sean D. Bradshaw
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Publication number: 20170184306Abstract: A combustor of a gas turbine engine including a combustor shell having an interior surface defining a combustion chamber, a first panel mounted to the interior surface at a first position, the first panel having a first surface and a first rail extending from the first surface toward the combustor shell, the first rail configured at a first angle relative to the first surface, and a second panel mounted to the interior surface at a second position axially adjacent to the first panel, the second panel having a second surface and a second rail extending from the second surface toward the combustor shell, the second rail configured at a second angle relative to the second surface. The first and second rails are proximal to each other and define a circumferential gap there between and at least one of the first or second angles is an acute angle.Type: ApplicationFiled: December 29, 2015Publication date: June 29, 2017Inventors: John S. Tu, James B. Hoke, Jonathan Jeffery Eastwood, Kevin Joseph Low, Sean D. Bradshaw
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Publication number: 20160273453Abstract: A cooling system for a fuel injector system of a gas turbine engine has a heat exchanger for cooling a portion of diffuser case air and then routing the cooled diffuser case air through a sleeve that surrounds a fuel injector conduit located in at least the diffuser case plenum for minimizing fuel heat-up rates in the conduit. By minimizing fuel temperatures within the injector conduit, coking accumulation is thereby eliminated or reduced.Type: ApplicationFiled: October 31, 2014Publication date: September 22, 2016Inventors: John D. Frish, Alexander W. Williams, Sean D. Bradshaw
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Publication number: 20160222794Abstract: This disclosure relates to a gas turbine engine including a component having a leading edge, a pressure side and a suction side opposite the pressure side. The component includes a first group of showerhead holes in the leading edge and a second group of showerhead holes in one of the pressure side and the suction side. The component further includes a first core passageway and a second core passageway separate from the first core passageway. The first core passageway and the second core passageway are in communication with a respective one of the first group of showerhead holes and the second group of showerhead holes.Type: ApplicationFiled: September 9, 2014Publication date: August 4, 2016Inventors: Thomas N. Slavens, Mark F. Zelesky, Atul Kohli, Sean D. Bradshaw, Steven Bruce Gautschi
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Publication number: 20160177735Abstract: A turbine blade includes a platform that has a platform leading edge and trailing edge joined by two platform circumferential sides. An airfoil extends radially outwardly from the platform to a free tip end. The airfoil includes an airfoil leading edge and trailing edge joined by opposed pressure and suction sides. A root extends radially inwardly from the platform. The platform and the airfoil include film cooling holes that have external breakout points that are located in substantial conformance with the Cartesian coordinates set forth in Table 1. The Cartesian coordinates provided by an axial coordinate, a circumferential coordinate, and a radial coordinate, relative to a zero-coordinate, and the cooling holes have a diametrical surface tolerance relative to the specified coordinates of 0.200 inches (5.0 mm).Type: ApplicationFiled: December 10, 2015Publication date: June 23, 2016Inventor: Sean D. Bradshaw