Patents by Inventor Chad Holden Sutton
Chad Holden Sutton 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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Publication number: 20230417412Abstract: A combustor assembly for a gas turbine engine includes a dome having a forward surface and an inner surface. The forward surface and the inner surface of the dome at least partially define a slot. The combustor assembly also includes a liner at least partially defining a combustion chamber and extending between an aft end and a forward end. The forward end of the liner is positioned within the slot of the dome. The forward end of the liner includes an axial interface surface and a radial interface surface. The axial interface surface defines a radial gap with the inner surface of the dome and the radial interface surface defines an axial gap with the forward surface of the dome. At least one of the radial gap or the axial gap is less than about 0.150 inches during operating conditions of the combustor assembly to prevent an undesirable airflow.Type: ApplicationFiled: April 28, 2023Publication date: December 28, 2023Inventors: Michael Alan Stieg, Gregory Scott Phelphs, Jeffrey Douglas Johnson, Chad Holden Sutton, Robert Andrew Stowers, Darrell Glenn Senile
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Patent number: 11725814Abstract: A combustor assembly for a gas turbine engine includes a dome having a forward surface and an inner surface. The forward surface and the inner surface of the dome at least partially define a slot. The combustor assembly also includes a liner at least partially defining a combustion chamber and extending between an aft end and a forward end. The forward end of the liner is positioned within the slot of the dome. The forward end of the liner includes an axial interface surface and a radial interface surface. The axial interface surface defines a radial gap with the inner surface of the dome and the radial interface surface defines an axial gap with the forward surface of the dome. At least one of the radial gap or the axial gap is less than about 0.150 inches during operating conditions of the combustor assembly to prevent an undesirable airflow.Type: GrantFiled: October 16, 2019Date of Patent: August 15, 2023Assignee: GENERAL. ELECTRIC COMPANYInventors: Michael Alan Stieg, Darrell Glenn Senile, Gregory Scott Phelps, Jeffrey Douglas Johnson, Chad Holden Sutton, Robert Andrew Stowers
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Publication number: 20210063016Abstract: A combustor assembly for a gas turbine engine includes a dome having a forward surface and an inner surface. The forward surface and the inner surface of the dome at least partially define a slot. The combustor assembly also includes a liner at least partially defining a combustion chamber and extending between an aft end and a forward end. The forward end of the liner is positioned within the slot of the dome. The forward end of the liner includes an axial interface surface and a radial interface surface. The axial interface surface defines a radial gap with the inner surface of the dome and the radial interface surface defines an axial gap with the forward surface of the dome. At least one of the radial gap or the axial gap is less than about 0.150 inches during operating conditions of the combustor assembly to prevent an undesirable airflow.Type: ApplicationFiled: October 16, 2019Publication date: March 4, 2021Inventors: Michael Alan Stieg, Darrell Glenn Senile, Gregory Scott Phelps, Jeffrey Douglas Johnson, Chad Holden Sutton, Robert Andrew Stowers
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Patent number: 10837640Abstract: A combustion section for gas turbine engine includes an inner liner, an outer liner, and a dome attached to the inner liner and to the outer liner. A heat shield is attached to the dome, with the dome, the heat shield, or both define an opening. The combustion section also includes a fuel nozzle extending at least partially into the opening, the fuel nozzle defining a fuel nozzle axis and a radial direction relative to the fuel nozzle axis. The fuel nozzle defines an aft end, the aft end of the fuel nozzle positioned forward of the aft surface of the heat shield along the fuel nozzle axis such that the aft end of the fuel nozzle defines a minimum separation from the aft surface of the heat shield along the fuel nozzle axis of at least about 0.15 inches.Type: GrantFiled: March 6, 2017Date of Patent: November 17, 2020Assignee: General Electric CompanyInventors: Nayan Vinodbhai Patel, Chad Holden Sutton, Duane Douglas Thomsen
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Publication number: 20190137101Abstract: A combustor assembly for a gas turbine engine is provided. The combustor assembly includes a liner at least partially defining a combustion chamber and extending between an aft end a forward end generally along an axial direction. The combustor assembly also includes an annular dome including an enclosed surface defining a slot for receipt of the forward end of the liner. A cap is positioned at the forward end of the liner and at least partially positioned within the slot defined by the enclosed surface of the annular dome. The cap includes a surface configured to contact at least one of the enclosed surface of the annular dome and the forward end of the liner. Such a configuration may form a substantially airtight seal between the forward end of the liner and the annular dome despite a relative thermal expansion between the components.Type: ApplicationFiled: December 21, 2018Publication date: May 9, 2019Inventors: Nicholas John Bloom, Daniel Kirtley, Michael Alan Stieg, Brian Christopher Towle, Chad Holden Sutton
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Patent number: 10197278Abstract: A combustor assembly for a gas turbine engine is provided. The combustor assembly includes a liner at least partially defining a combustion chamber and extending between an aft end a forward end generally along an axial direction. The combustor assembly also includes an annular dome including an enclosed surface defining a slot for receipt of the forward end of the liner. A cap is positioned at the forward end of the liner and at least partially positioned within the slot defined by the enclosed surface of the annular dome. The cap includes a surface configured to contact at least one of the enclosed surface of the annular dome and the forward end of the liner. Such a configuration may form a substantially airtight seal between the forward end of the liner and the annular dome despite a relative thermal expansion between the components.Type: GrantFiled: September 2, 2015Date of Patent: February 5, 2019Assignee: General Electric CompanyInventors: Nicholas John Bloom, Daniel Kirtley, Michael Alan Stieg, Brian Christopher Towle, Chad Holden Sutton
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Publication number: 20180356095Abstract: A combustion section for gas turbine engine includes an inner liner, an outer liner, and a dome attached to the inner liner and to the outer liner. A heat shield is attached to the dome, with the dome, the heat shield, or both define an opening. The combustion section also includes a fuel nozzle extending at least partially into the opening, the fuel nozzle defining a fuel nozzle axis and a radial direction relative to the fuel nozzle axis. The fuel nozzle defines an aft end, the aft end of the fuel nozzle positioned forward of the aft surface of the heat shield along the fuel nozzle axis such that the aft end of the fuel nozzle defines a minimum separation from the aft surface of the heat shield along the fuel nozzle axis of at least about 0.15 inches.Type: ApplicationFiled: March 6, 2017Publication date: December 13, 2018Inventors: Nayan Vinodbhai Patel, Chad Holden Sutton, Duane Douglas Thomsen
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Patent number: 10041676Abstract: A combustor assembly for a gas turbine engine defining an axial direction is provided. The combustor assembly generally includes a liner, an annular dome, and a deflector plate. The liner at least partially defines a combustion chamber. The annular dome defines a first cavity and has a plurality of impingement holes, and the deflector plate defines a conical surface and a flat surface, wherein a plurality of cooling holes are defined through the deflector plate. The annular dome and the deflector plate are positioned together to define a second cavity that is in fluid communication with the first cavity through the plurality of impingement holes. In addition, the second cavity is in fluid communication with the combustion chamber through the plurality of cooling holes.Type: GrantFiled: July 8, 2015Date of Patent: August 7, 2018Assignee: General Electric CompanyInventors: Nayan Vinodbhai Patel, Kwanwoo Kim, Chad Holden Sutton, Duane Douglas Thomsen, Craig Alan Gonyou, Harris Daniel Abramson, James A. Russo, Robert Andrew Stowers, Shanwu Wang, Anquan Wang
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Publication number: 20180051880Abstract: A combustor assembly for a gas turbine engine includes a dome having a forward surface and an inner surface. The forward surface and the inner surface of the dome at least partially define a slot. The combustor assembly also includes a liner at least partially defining a combustion chamber and extending between an aft end and a forward end. The forward end of the liner is positioned within the slot of the dome. The forward end of the liner includes an axial interface surface and a radial interface surface. The axial interface surface defines a radial gap with the inner surface of the dome and the radial interface surface defines an axial gap with the forward surface of the dome. At least one of the radial gap or the axial gap is less than about 0.150 inches during operating conditions of the combustor assembly to prevent an undesirable airflow.Type: ApplicationFiled: August 18, 2016Publication date: February 22, 2018Inventors: Michael Alan Stieg, Darrell Glenn Senile, Gregory Scott Phelps, Jeffrey Douglas Johnson, Chad Holden Sutton, Robert Andrew Stowers
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Publication number: 20170059160Abstract: A combustor assembly for a gas turbine engine is provided. The combustor assembly includes a liner at least partially defining a combustion chamber and extending between an aft end a forward end generally along an axial direction. The combustor assembly also includes an annular dome including an enclosed surface defining a slot for receipt of the forward end of the liner. A cap is positioned at the forward end of the liner and at least partially positioned within the slot defined by the enclosed surface of the annular dome. The cap includes a surface configured to contact at least one of the enclosed surface of the annular dome and the forward end of the liner. Such a configuration may form a substantially airtight seal between the forward end of the liner and the annular dome despite a relative thermal expansion between the components.Type: ApplicationFiled: September 2, 2015Publication date: March 2, 2017Inventors: Nicholas John Bloom, Daniel Kirtley, Michael Alan Stieg, Brian Christopher Towle, Chad Holden Sutton
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Publication number: 20170009986Abstract: A combustor assembly for a gas turbine engine defining an axial direction is provided. The combustor assembly generally includes a liner, an annular dome, and a deflector plate. The liner at least partially defines a combustion chamber. The annular dome defines a first cavity and has a plurality of impingement holes, and the deflector plate defines a conical surface and a flat surface, wherein a plurality of cooling holes are defined through the deflector plate. The annular dome and the deflector plate are positioned together to define a second cavity that is in fluid communication with the first cavity through the plurality of impingement holes. In addition, the second cavity is in fluid communication with the combustion chamber through the plurality of cooling holes.Type: ApplicationFiled: July 8, 2015Publication date: January 12, 2017Inventors: Nayan Vinodbhai Patel, Kwanwoo Kim, Chad Holden Sutton, Duane Douglas Thomsen, Craig Alan Gonyou, Harris Daniel Abramson, James A. Russo, Robert Andrews Stowers, Shanwu Wang, Anquan Wang