Patents by Inventor Douglas Dailey
Douglas Dailey 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: 11959393Abstract: An airfoil assembly for a turbine engine comprising an outer band, an inner band radially spaced inwardly from the outer band to define an annular region, and multiple airfoils circumferentially spaced within the annular region. Each corresponding airfoil of the multiple airfoils can project from a surface at a root and can further include an outer wall defining a pressure side and a suction side. A projection can extend upwardly from the surface on the pressure side and a valley can extend into the surface on the suction side to define a contour in the surface.Type: GrantFiled: November 10, 2021Date of Patent: April 16, 2024Assignees: General Electric Company, GE Avivo S.r.l.Inventors: Saurya Ranjan Ray, Francesco Bertini, Lyle Douglas Dailey, Jeffrey D. Clements, Jaikumar Loganathan, Simone Rosa Taddei
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Patent number: 11885233Abstract: A turbine engine with at least a compressor section, combustor section, turbine section and a set of airfoils. The airfoils include geometric characteristics to create a high contraction ratio (CR), a low blade turning (BT) at a radially inward location the airfoil, a low solidity, or a low aspect ratio (AR).Type: GrantFiled: July 28, 2022Date of Patent: January 30, 2024Assignees: General Electric Company, GE Avio S.r.l.Inventors: Ernesto Sozio, Francesco Bertini, Jeffrey Donald Clements, Jonathan Ong, Lyle Douglas Dailey, Paul Hadley Vitt, Matteo Renato Usseglio
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Publication number: 20230374935Abstract: A turbine section for a gas turbine engine defines a radial direction and includes a low-pressure (LP) turbine that includes a first plurality of LP turbine blades that includes a first stage having first stage LP turbine blades that rotate in a first direction at a first speed, a second plurality of LP turbine blades that includes a plurality of stages of LP turbine blades disposed downstream of the first stage LP turbine blades that rotate in a second direction opposite the first direction at a second speed, a first LP turbine spool connected to the first plurality of LP turbine blades on an inner side of the first plurality of LP turbine blades in the radial direction, and a second LP turbine spool connected to the second plurality of LP turbine blades on an inner side of the second plurality of LP turbine blades in the radial directionType: ApplicationFiled: May 18, 2022Publication date: November 23, 2023Inventors: Paul Hadley Vitt, Lyle Douglas Dailey, Matteo Renato Usseglio, Andreas Peters
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Publication number: 20230340906Abstract: A turbine section and an exhaust section for a gas turbine engine includes a low pressure (LP) turbine having first stage LP turbine blades that rotate in a first direction at a first speed, and final stage LP turbine blades downstream of the first stage LP turbine blades that rotate in a second direction opposite the first direction at a second speed. The second speed is lower than the first speed.Type: ApplicationFiled: April 5, 2022Publication date: October 26, 2023Inventors: Paul Hadley Vitt, Lyle Douglas Dailey, Matteo Renato Usseglio, Andreas Peters, Jonathan Ong
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Publication number: 20230130213Abstract: A turbine engine with at least a compressor section, combustor section, turbine section and a set of airfoils. The airfoils include geometric characteristics to create a high contraction ratio (CR), a low blade turning (BT) at a radially inward location the airfoil, a low solidity, or a low aspect ratio (AR).Type: ApplicationFiled: July 28, 2022Publication date: April 27, 2023Inventors: Ernesto Sozio, Francesco Bertini, Jeffrey Donald Clements, Jonathan Ong, Lyle Douglas Dailey, Paul Hadley Vitt, Matteo Renato Usseglio
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Patent number: 11434765Abstract: A turbine engine with at least a compressor section, combustor section, turbine section and a set of airfoils. The airfoils include geometric characteristics to create a high contraction ratio (CR), a low blade turning (BT) at a radially inward location the airfoil, a low solidity, or a low aspect ratio (AR).Type: GrantFiled: January 14, 2021Date of Patent: September 6, 2022Assignees: General Electric Company, GE AVIO S.r.l.Inventors: Ernesto Sozio, Francesco Bertini, Jeffrey Donald Clements, Jonathan Ong, Lyle Douglas Dailey, Paul Hadley Vitt, Matteo Renato Usseglio
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Publication number: 20220243596Abstract: An airfoil assembly for a turbine engine comprising an outer band, an inner band radially spaced inwardly from the outer band to define an annular region, and multiple airfoils circumferentially spaced within the annular region. Each corresponding airfoil of the multiple airfoils can project from a surface at a root and can further include an outer wall defining a pressure side and a suction side. A projection can extend upwardly from the surface on the pressure side and a valley can extend into the surface on the suction side to define a contour in the surface.Type: ApplicationFiled: November 10, 2021Publication date: August 4, 2022Inventors: Saurya Ranjan Ray, Francesco Bertini, Lyle Douglas Dailey, Jeffrey D. Clements, Jaikumar Loganathan, Simone Rosa Taddei
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Patent number: 11274563Abstract: A turbine rear frame for a gas turbine engine comprises a plurality of struts disposed between an outer ring and an inner ring. The struts can be mounted adjacent to one or more mount surfaces defined within the outer ring. The mount surface can comprise a recess in the outer ring having a maximum radial distance upstream of engine mounts inserted therein. The struts can further comprise a pitch angle offset from a centerline of the mount surface and a tangentially curved trailing edge at a tip to improve aerodynamic performance of the turbine rear frame.Type: GrantFiled: January 21, 2016Date of Patent: March 15, 2022Assignee: General Electric CompanyInventors: Mohsin Hasan Khan, Sarasija Sudharsan, Ganesh Seshadri, Ravikanth Avancha, Lyle Douglas Dailey
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Publication number: 20210270137Abstract: A turbine engine with at least a compressor section, combustor section, turbine section and a set of airfoils. The airfoils include geometric characteristics to create a high contraction ratio (CR), a low blade turning (BT) at a radially inward location the airfoil, a low solidity, or a low aspect ratio (AR).Type: ApplicationFiled: January 14, 2021Publication date: September 2, 2021Inventors: Ernesto Sozio, Francesco Bertini, Jeffrey Donald Clements, Jonathan Ong, Lyle Douglas Dailey, Paul Hadley Vitt, Matteo Renato Usseglio
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Patent number: 10502721Abstract: A temperature controller for simultaneously controlling the temperatures of a plurality of heating elements for use in chromatographic analysis including columns, detectors, valves, transport lines and other components.Type: GrantFiled: May 14, 2019Date of Patent: December 10, 2019Assignee: Valco Instruments Company, L.P.Inventors: Stanley D. Stearns, Huamin Cai, Chris Bishop, Robert Simpson, Chris S. Cowles, Dale Ashworth, Douglas Dailey
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Patent number: 10481137Abstract: A temperature controller for simultaneously controlling the temperatures of a plurality of heating elements for use in chromatographic analysis including columns, detectors, valves, transport lines and other components.Type: GrantFiled: July 2, 2019Date of Patent: November 19, 2019Assignee: Valco Instruments Company, L.P.Inventors: Stanley D. Stearns, Huamin Cai, Chris Bishop, Robert Simpson, Chris S. Cowles, Dale Ashworth, Douglas Dailey
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Patent number: 10481136Abstract: A temperature controller for simultaneously controlling the temperatures of a plurality of heating elements for use in chromatographic analysis including columns, detectors, valves, transport lines and other components.Type: GrantFiled: May 14, 2019Date of Patent: November 19, 2019Assignee: Valco Instruments Company, L.P.Inventors: Stanley D. Stearns, Huamin Cai, Chris Bishop, Robert Simpson, Chris S. Cowles, Dale Ashworth, Douglas Dailey
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Publication number: 20190323999Abstract: A temperature controller for simultaneously controlling the temperatures of a plurality of heating elements for use in chromatographic analysis including columns, detectors, valves, transport lines and other components.Type: ApplicationFiled: July 2, 2019Publication date: October 24, 2019Applicant: Valco Instruments Company, L.P.Inventors: Stanley D. Stearns, Huamin Cai, Chris Bishop, Robert Simpson, Chris S. Cowles, Dale Ashworth, Douglas Dailey
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Publication number: 20190265209Abstract: A temperature controller for simultaneously controlling the temperatures of a plurality of heating elements for use in chromatographic analysis including columns, detectors, valves, transport lines and other components.Type: ApplicationFiled: May 14, 2019Publication date: August 29, 2019Applicant: Valco Instruments Company, L.P.Inventors: Stanley D. Stearns, Huamin Cai, Chris Bishop, Robert Simpson, Chris S. Cowles, Dale Ashworth, Douglas Dailey
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Publication number: 20190265208Abstract: A temperature controller for simultaneously controlling the temperatures of a plurality of heating elements for use in chromatographic analysis including columns, detectors, valves, transport lines and other components.Type: ApplicationFiled: May 14, 2019Publication date: August 29, 2019Applicant: Valco Instruments Company, L.P.Inventors: Stanley D. Stearns, Huamin Cai, Chris Bishop, Robert Simpson, Chris S. Cowles, Dale Ashworth, Douglas Dailey
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Patent number: 10324069Abstract: A temperature controller for simultaneously controlling the temperatures of a plurality of heating elements for use in chromatographic analysis including columns, detectors, valves, transport lines and other components.Type: GrantFiled: February 24, 2017Date of Patent: June 18, 2019Assignee: Valco Instruments Company, L.P.Inventors: Stanley D. Stearns, Huamin Cai, Chris Bishop, Robert Simpson, Chris S. Cowles, Dale Ashworth, Douglas Dailey
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Publication number: 20180347403Abstract: An apparatus and method for a turbine engine comprising an outer casing having a first surface and defining an axial centerline and an inner casing located within the outer casing and having a second surface spaced. The first and second surfaces are spaced from each other and define an annular channel between where a combustion air flows in a fore to aft direction along a profile.Type: ApplicationFiled: May 31, 2017Publication date: December 6, 2018Inventors: Mahendran Manoharan, Ganesh Seshadri, Robert J. Beacock, Lyle Douglas Dailey, Ravikanth Avancha
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Publication number: 20180246074Abstract: A temperature controller for simultaneously controlling the temperatures of a plurality of heating elements for use in chromatographic analysis including columns, detectors, valves, transport lines and other components.Type: ApplicationFiled: February 24, 2017Publication date: August 30, 2018Applicant: Valco Instruments Company, L.P.Inventors: Stanley D. Stearns, Huamin Cai, Chris Bishop, Robert Simpson, Chris S. Cowles, Dale Ashworth, Douglas Dailey
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Publication number: 20170211399Abstract: A turbine rear frame for a gas turbine engine comprises a plurality of struts disposed between an outer ring and an inner ring. The struts can be mounted adjacent to one or more mount surfaces defined within the outer ring. The mount surface can comprise a recess in the outer ring having a maximum radial distance upstream of engine mounts inserted therein. The struts can further comprise a pitch angle offset from a centerline of the mount surface and a tangentially curved trailing edge at a tip to improve aerodynamic performance of the turbine rear frame.Type: ApplicationFiled: January 21, 2016Publication date: July 27, 2017Inventors: Mohsin Hasan Khan, Sarasija Sudharsan, Ganesh Seshadri, Ravikanth Avancha, Lyle Douglas Dailey
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Publication number: 20170138202Abstract: Turbine assemblies for gas turbine engines are provided. In one embodiment, a turbine assembly includes a row of circumferentially adjacent turbine rotor blades, each blade in the row of blades including an airfoil defining a chord extending axially between opposite leading and trailing edges of the airfoil. The chords in a mid-span region of each blade are shorter than the chords in span regions adjacent to the blade root and the blade tip. In another exemplary embodiment, a turbine assembly includes a row of circumferentially adjacent turbine stator vanes, each vane in the row of vanes including an airfoil defining a chord extending axially between opposite leading and trailing edges of the airfoil. The chords in a mid-span region of each vane are shorter than the chords in span regions adjacent to the vane root and the vane tip. A turbine rotor blade for a gas turbine engine also is provided.Type: ApplicationFiled: November 16, 2015Publication date: May 18, 2017Inventors: Aspi Rustom Wadia, Lyle Douglas Dailey, Christopher Ryan Johnson, Daniel Mollmann