Patents by Inventor David Albin Lind
David Albin Lind 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: 11156361Abstract: The present disclosure is directed to a fuel injector for a gas turbine engine. The fuel injector includes an end wall, a centerbody, an outer sleeve surrounding the centerbody from the end wall toward the downstream end of the fuel injector, and a thermal management conduit. The centerbody includes an axially extended outer wall and inner wall extended from the end wall toward a downstream end of the fuel injector. The outer wall, the inner wall, and the end wall together define a fluid conduit extended in a first direction toward the downstream end of the fuel injector and in a second direction toward an upstream end of the fuel injector. The outer sleeve and the centerbody define a premix passage radially therebetween and an outlet at the downstream end of the premix passage. The outer sleeve defines a plurality of radially oriented first air inlet ports in circumferential arrangement at a first axial portion of the outer sleeve.Type: GrantFiled: July 19, 2019Date of Patent: October 26, 2021Assignee: GENERAL ELECTRIC COMPANYInventors: Gregory Allen Boardman, Pradeep Naik, Manampathy Gangadharan Giridharan, David Albin Lind, Jeffrey Michael Martini, Clayton S. Cooper
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Patent number: 11067280Abstract: The present disclosure is directed to a method for operating a turbine engine, the method including arranging a fluid conduit through a fuel nozzle in a first direction toward a downstream end and in a second direction toward an upstream end, the fluid conduit in fluid communication with a premix passage via a fluid injection port; flowing an oxidizer into the premix passage via a radially oriented first inlet port and a radially oriented second inlet port; flowing a first fuel to the premix passage through the fluid conduit and the fluid injection port, wherein the first fuel is provided to the premix passage axially downstream of the first inlet port; and generating a premixed flame from a mixture of the oxidizer and the first fuel.Type: GrantFiled: April 5, 2019Date of Patent: July 20, 2021Assignee: GENERAL ELECTRIC COMPANYInventors: Gregory Allen Boardman, Pradeep Naik, Manampathy Gangadharan Giridharan, David Albin Lind, Jeffrey Michael Martini
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Patent number: 10895384Abstract: A fuel injector assembly for a gas turbine engine is generally provided. The first fuel injector includes a first centerbody surrounding a first walled fuel injection circuit. A first fuel injection port is extended at least partially radially through the first centerbody in fluid communication with the first walled fuel injection circuit. The first centerbody defines a cooling circuit surrounding the first walled fuel injection circuit. The first centerbody defines a plurality of cooling openings at a downstream end of the first centerbody. The plurality of cooling openings is in fluid communication with the cooling circuit. The first centerbody defines an axially extended cooling outlet at the downstream end of the first centerbody.Type: GrantFiled: November 29, 2018Date of Patent: January 19, 2021Assignee: GENERAL ELECTRIC COMPANYInventors: Randall Charles Boehm, Gregory Allen Boardman, Ajoy Patra, David Albin Lind, Pradeep Naik, Ranjeet Kumar Mishra
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Patent number: 10816210Abstract: A fuel injector assembly for a gas turbine engine includes a centerbody extended along a lengthwise direction, the centerbody defining a first fuel nozzle, and an annular shroud defining a second fuel nozzle directly surrounding the centerbody and extended along the lengthwise direction. A passage is defined through the annular shroud and extended generally along the lengthwise direction. The passage defines an exit opening disposed at a downstream end adjacent to the combustion chamber and in fluid communication therewith. The annular shroud defines a fuel inlet opening disposed at an upstream end of the passage. The annular shroud defines an air inlet opening in fluid communication with the passage. The air inlet opening is disposed between the fuel inlet opening and the exit opening.Type: GrantFiled: September 28, 2017Date of Patent: October 27, 2020Assignee: General Electric CompanyInventors: David Albin Lind, Gregory Allen Boardman
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Publication number: 20200173662Abstract: A fuel injector assembly for a gas turbine engine is generally provided. The first fuel injector includes a first centerbody surrounding a first walled fuel injection circuit. A first fuel injection port is extended at least partially radially through the first centerbody in fluid communication with the first walled fuel injection circuit. The first centerbody defines a cooling circuit surrounding the first walled fuel injection circuit. The first centerbody defines a plurality of cooling openings at a downstream end of the first centerbody. The plurality of cooling openings is in fluid communication with the cooling circuit. The first centerbody defines an axially extended cooling outlet at the downstream end of the first centerbody.Type: ApplicationFiled: November 29, 2018Publication date: June 4, 2020Inventors: Randall Charles Boehm, Gregory Allen Boardman, Ajoy Patra, David Albin Lind, Pradeep Naik, Ranjeet Kumar Mishra
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Patent number: 10598380Abstract: The present disclosure is directed to a combustion section for a gas turbine engine including a combustor assembly, an outer casing, a fuel injector assembly, and an inner casing. An inner liner and an outer liner are each extended at least partially along a lengthwise direction and at an acute angle. A dome assembly is extended between the inner liner and the outer liner, and the inner liner, and the outer liner together define a combustion chamber therebetween. A bulkhead assembly defining a plurality of walls is coupled to the inner liner and generally surrounding the outer liner and dome assembly. The outer casing surrounds the combustor assembly. The inner casing, the outer casing, and the combustor assembly together define a primary flowpath. An oxidizer flows through the primary flowpath in serial flow through the plenum and the fuel injector assembly into the combustion chamber.Type: GrantFiled: September 21, 2017Date of Patent: March 24, 2020Assignee: General Electric CompanyInventors: David Albin Lind, Rishikesh Karande, Pradeep Naik, Ajoy Patra, Gregory Allen Boardman
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Publication number: 20200025385Abstract: The present disclosure is directed to a method for operating a turbine engine, the method including arranging a fluid conduit through a fuel nozzle in a first direction toward a downstream end and in a second direction toward an upstream end, the fluid conduit in fluid communication with a premix passage via a fluid injection port; flowing an oxidizer into the premix passage via a radially oriented first inlet port and a radially oriented second inlet port; flowing a first fuel to the premix passage through the fluid conduit and the fluid injection port, wherein the first fuel is provided to the premix passage axially downstream of the first inlet port; and generating a premixed flame from a mixture of the oxidizer and the first fuel.Type: ApplicationFiled: April 5, 2019Publication date: January 23, 2020Inventors: Gregory Allen Boardman, Pradeep Naik, Manampathy Gangadharan Giridharan, David Albin Lind, Jeffrey Michael Martini
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Publication number: 20190346141Abstract: The present disclosure is directed to a fuel injector for a gas turbine engine. The fuel injector includes an end wall, a centerbody, an outer sleeve surrounding the centerbody from the end wall toward the downstream end of the fuel injector, and a thermal management conduit. The centerbody includes an axially extended outer wall and inner wall extended from the end wall toward a downstream end of the fuel injector. The outer wall, the inner wall, and the end wall together define a fluid conduit extended in a first direction toward the downstream end of the fuel injector and in a second direction toward an upstream end of the fuel injector. The outer sleeve and the centerbody define a premix passage radially therebetween and an outlet at the downstream end of the premix passage. The outer sleeve defines a plurality of radially oriented first air inlet ports in circumferential arrangement at a first axial portion of the outer sleeve.Type: ApplicationFiled: July 19, 2019Publication date: November 14, 2019Inventors: Gregory Allen Boardman, Pradeep Naik, Manampathy Gangadharan Giridharan, David Albin Lind, Jeffrey Michael Martini, Clayton S. Cooper
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Patent number: 10393382Abstract: The present disclosure is directed to a fuel injector for a gas turbine engine. The fuel injector includes an end wall, a centerbody, an outer sleeve surrounding the centerbody from the end wall toward the downstream end of the fuel injector, and a thermal management conduit. The centerbody includes an axially extended outer wall and inner wall extended from the end wall toward a downstream end of the fuel injector. The outer wall, the inner wall, and the end wall together define a fluid conduit extended in a first direction toward the downstream end of the fuel injector and in a second direction toward an upstream end of the fuel injector. The outer sleeve and the centerbody define a premix passage radially therebetween and an outlet at the downstream end of the premix passage. The outer sleeve defines a plurality of radially oriented first air inlet ports in circumferential arrangement at a first axial portion of the outer sleeve.Type: GrantFiled: November 4, 2016Date of Patent: August 27, 2019Assignee: General Electric CompanyInventors: Gregory Allen Boardman, Pradeep Naik, Manampathy Gangadharan Giridharan, David Albin Lind, Jeffrey Michael Martini, Clayton S. Cooper
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Patent number: 10352569Abstract: The present disclosure is directed to a fuel injector for a gas turbine engine. The fuel injector includes an end wall defining a fluid chamber, a centerbody, an outer sleeve surrounding the centerbody from the end wall toward a downstream end of the fuel injector, and a fluid cavity wall. The centerbody includes an axially extended outer wall and inner wall extended from the end wall toward the downstream end of the fuel injector. The outer wall, the inner wall, and the end wall together define a fluid conduit extended in a first direction toward the downstream end of the fuel injector and in a second direction toward an upstream end of the fuel injector. The fluid conduit is in fluid communication with the fluid chamber. The outer wall defines at least one radially oriented fluid injection port in fluid communication with the fluid conduit. The outer sleeve and the centerbody define a premix passage radially therebetween and an outlet at the downstream end of the premix passage.Type: GrantFiled: November 4, 2016Date of Patent: July 16, 2019Assignee: General Electric CompanyInventors: Gregory Allen Boardman, Pradeep Naik, Manampathy Gangadharan Giridharan, David Albin Lind, Jeffrey Michael Martini
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Patent number: 10295190Abstract: The present disclosure is directed to a fuel injector for a gas turbine engine including an end wall defining a fluid chamber, a centerbody, and an outer sleeve surrounding the centerbody from the end wall toward a downstream end of the fuel injector. The centerbody includes an axially extended outer wall and inner wall. The outer wall and inner wall extend from the end wall toward the downstream end of the fuel injector. The outer wall, the inner wall, and the end wall together define a fluid conduit extended in a first direction toward the downstream end of the fuel injector and in a second direction toward an upstream end of the fuel injector. The fluid conduit is in fluid communication with the fluid chamber. The outer wall defines at least one radially oriented fluid injection port in fluid communication with the fluid conduit. The outer sleeve and the centerbody define a premix passage radially therebetween and an outlet at the downstream end of the premix passage.Type: GrantFiled: November 4, 2016Date of Patent: May 21, 2019Assignee: General Electric CompanyInventors: Gregory Allen Boardman, Pradeep Naik, Manampathy Gangadharan Giridharan, David Albin Lind, Jeffrey Michael Martini
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Publication number: 20190093895Abstract: The present disclosure is directed to a fuel injector assembly and a gas turbine engine including the fuel injector assembly. The fuel injector assembly includes a centerbody extended along a lengthwise direction. The centerbody defines a first fuel nozzle. An annular shroud defining a second fuel nozzle surrounds the centerbody and is extended along the lengthwise direction. A passage is defined through the annular shroud and extended generally along the lengthwise direction. The passage defines an exit opening disposed at a downstream end adjacent to the combustion chamber and in fluid communication therewith. The annular shroud defines a fuel inlet opening disposed at an upstream end of the passage. The annular shroud further defines an air inlet opening in fluid communication with the passage. The air inlet opening is disposed between the fuel inlet opening and the exit opening.Type: ApplicationFiled: September 28, 2017Publication date: March 28, 2019Inventors: David Albin Lind, Gregory Allen Boardman
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Publication number: 20190086085Abstract: The present disclosure is directed to a combustion section for a gas turbine engine. The combustion section includes a combustor assembly, an outer casing, a fuel injector assembly, and an inner casing. The combustor assembly includes an inner liner and an outer liner each extended at least partially along a lengthwise direction and at an acute angle relative to the longitudinal centerline. The combustor assembly further includes a dome assembly extended between the inner liner and the outer liner. The dome assembly, the inner liner, and the outer liner together define a combustion chamber therebetween. The combustor assembly still further includes a bulkhead assembly defining a plurality of walls coupled to the inner liner and generally surrounding the outer liner and dome assembly. At least a portion of the bulkhead assembly is extended at least partially along a forward direction and defines a plenum between the bulkhead assembly and the dome assembly.Type: ApplicationFiled: September 21, 2017Publication date: March 21, 2019Inventors: David Albin Lind, Rishikesh Karande, Pradeep Naik, Ajoy Patra, Gregory Allen Boardman
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Publication number: 20180128491Abstract: The present disclosure is directed to a fuel injector for a gas turbine engine. The fuel injector includes an end wall defining a fluid chamber, a centerbody, an outer sleeve surrounding the centerbody from the end wall toward a downstream end of the fuel injector, and a fluid cavity wall. The centerbody includes an axially extended outer wall and inner wall extended from the end wall toward the downstream end of the fuel injector. The outer wall, the inner wall, and the end wall together define a fluid conduit extended in a first direction toward the downstream end of the fuel injector and in a second direction toward an upstream end of the fuel injector. The fluid conduit is in fluid communication with the fluid chamber. The outer wall defines at least one radially oriented fluid injection port in fluid communication with the fluid conduit. The outer sleeve and the centerbody define a premix passage radially therebetween and an outlet at the downstream end of the premix passage.Type: ApplicationFiled: November 4, 2016Publication date: May 10, 2018Inventors: Gregory Allen Boardman, Pradeep Naik, Manampathy Gangadharan Giridharan, David Albin Lind, Jeffrey Michael Martini
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Publication number: 20180128489Abstract: The present disclosure is directed to a fuel injector for a gas turbine engine including an end wall defining a fluid chamber, a centerbody, and an outer sleeve surrounding the centerbody from the end wall toward a downstream end of the fuel injector. The centerbody includes an axially extended outer wall and inner wall. The outer wall and inner wall extend from the end wall toward the downstream end of the fuel injector. The outer wall, the inner wall, and the end wall together define a fluid conduit extended in a first direction toward the downstream end of the fuel injector and in a second direction toward an upstream end of the fuel injector. The fluid conduit is in fluid communication with the fluid chamber. The outer wall defines at least one radially oriented fluid injection port in fluid communication with the fluid conduit. The outer sleeve and the centerbody define a premix passage radially therebetween and an outlet at the downstream end of the premix passage.Type: ApplicationFiled: November 4, 2016Publication date: May 10, 2018Inventors: Gregory Allen Boardman, Pradeep Naik, Manampathy Gangadharan Giridharan, David Albin Lind, Jeffrey Michael Martini
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Publication number: 20180128490Abstract: The present disclosure is directed to a fuel injector for a gas turbine engine. The fuel injector includes an end wall, a centerbody, an outer sleeve surrounding the centerbody from the end wall toward the downstream end of the fuel injector, and a thermal management conduit. The centerbody includes an axially extended outer wall and inner wall extended from the end wall toward a downstream end of the fuel injector. The outer wall, the inner wall, and the end wall together define a fluid conduit extended in a first direction toward the downstream end of the fuel injector and in a second direction toward an upstream end of the fuel injector. The outer sleeve and the centerbody define a premix passage radially therebetween and an outlet at the downstream end of the premix passage. The outer sleeve defines a plurality of radially oriented first air inlet ports in circumferential arrangement at a first axial portion of the outer sleeve.Type: ApplicationFiled: November 4, 2016Publication date: May 10, 2018Inventors: Gregory Allen Boardman, Pradeep Naik, Manampathy Gangadharan Giridharan, David Albin Lind, Jeffrey Michael Martini, Clayton S. Cooper
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Patent number: 9719685Abstract: A system and method for flame stabilization is provided that forestalls incipient lean blow out by improving flame stabilization. A combustor profile is selected that maintains desired levels of power output while minimizing or eliminating overboard air bleed and minimizing emissions. The selected combustor profile maintains average shaft power in a range of from approximately 50% up to full power while eliminating overboard air bleed in maintaining such power settings. Embodiments allow for a combustor to operate with acceptable emissions at lower flame temperature. Because the combustor can operate at lower bulk flame temperatures during part power operation, the usage of inefficient overboard bleed can be reduced or even eliminated.Type: GrantFiled: July 25, 2012Date of Patent: August 1, 2017Assignee: General Electric CompanyInventors: Mark David Durbin, Mark Anthony Mueller, Lance Kenneth Blakeman, David Albin Lind
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Publication number: 20130152597Abstract: A system and method for flame stabilization is provided that forestalls incipient lean blow out by improving flame stabilization. A combustor profile is selected that maintains desired levels of power output while minimizing or eliminating overboard air bleed and minimizing emissions. The selected combustor profile maintains average shaft power in a range of from approximately 50% up to full power while eliminating overboard air bleed in maintaining such power settings. Embodiments allow for a combustor to operate with acceptable emissions at lower flame temperature. Because the combustor can operate at lower bulk flame temperatures during part power operation, the usage of inefficient overboard bleed can be reduced or even eliminated.Type: ApplicationFiled: July 25, 2012Publication date: June 20, 2013Applicant: GENERAL ELECTRIC COMPANYInventors: Mark David Durbin, Mark Anthony Mueller, Lance Kenneth Blakeman, David Albin Lind
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Patent number: 7086232Abstract: A liner for a combustor of a gas turbine engine, including a shell having a first end adjacent to an upstream end of the combustor and a second end adjacent to a downstream end of the combustor, wherein at least one discrete region is subject to distress from impingement of hot gases, a plurality of cooling slots formed in the shell through which air flows for providing a cooling film along a hot side of the shell, and a group of cooling holes formed in the shell in the discrete region to augment the cooling film and provide convective bore cooling to the discrete region.Type: GrantFiled: April 29, 2002Date of Patent: August 8, 2006Assignee: General Electric CompanyInventors: George Eric Moertle, Bruce Ernest Mills, James Patrick Holmes, David Albin Lind, Tariz Kay Harris
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Publication number: 20030200752Abstract: A liner for a combustor of a gas turbine engine, including a shell having a first end adjacent to an upstream end of the combustor and a second end adjacent to a downstream end of the combustor, wherein at least one discrete region is subject to distress from impingement of hot gases, a plurality of cooling slots formed in the shell through which air flows for providing a cooling film along a hot side of the shell, and a group of cooling holes formed in the shell in the discrete region to augment the cooling film and provide convective bore cooling to the discrete region.Type: ApplicationFiled: April 29, 2002Publication date: October 30, 2003Inventors: George Eric Moertle, Bruce Ernest Mills, James Patrick Holmes, David Albin Lind, Tariq Kay Harris