Patents by Inventor Michael Alan Stieg
Michael Alan Stieg 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: 11920789Abstract: A combustor assembly for a gas turbine engine includes an outer liner that at least partially defines a combustion chamber. The outer liner extends between an aft end and a forward end generally along an axial direction within an outer casing of the gas turbine engine. The outer liner includes an inner surface facing the combustion chamber and an outer surface facing away from the combustion chamber. The combustor assembly includes a radial damper assembly disposed against the outer liner at a plurality of circumferential points.Type: GrantFiled: February 4, 2021Date of Patent: March 5, 2024Assignee: General Electric CompanyInventors: Mark Willard Marusko, Michael Alan Stieg, Brian Christopher Towle
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Patent number: 11898494Abstract: A gas turbine engine is provided having a combustion section with a liner extending between a forward end and an aft end. A structural member is positioned in or around at least a portion of the combustion section. Additionally, a piston ring holder is provided attached to the structural member at a first end and positioned proximate to the aft end of the liner at a second end. The piston ring holder is a bimetallic member including a first portion formed of a first material and a second portion formed of a second material. A coefficient of thermal expansion of the first material is different than a coefficient of thermal expansion of the second material.Type: GrantFiled: October 15, 2021Date of Patent: February 13, 2024Assignee: General Electric CompanyInventors: Nicholas John Bloom, Michael Alan Stieg, Brian Christopher Towle
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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: 20220333778Abstract: A combustor assembly for a gas turbine engine includes a dome defining 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 is received within the slot of the dome. In one exemplary aspect, the combustor assembly includes features that warm the forward end of the liner during transient operation of the engine. Furthermore, the combustor assembly includes features that reduce the thermal gradient between the forward end and the other portions of the liner. In this way, improved durability of the liner may be achieved.Type: ApplicationFiled: July 1, 2022Publication date: October 20, 2022Inventors: Michael Alan Stieg, Nicholas John Bloom
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Patent number: 11402097Abstract: A combustor assembly for a gas turbine engine includes a dome defining 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 is received within the slot of the dome. In one exemplary aspect, the combustor assembly includes features that warm the forward end of the liner during transient operation of the engine. Furthermore, the combustor assembly includes features that reduce the thermal gradient between the forward end and the other portions of the liner. In this way, improved durability of the liner may be achieved.Type: GrantFiled: January 3, 2018Date of Patent: August 2, 2022Assignee: General Electric CompanyInventors: Michael Alan Stieg, Nicholas John Bloom
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Publication number: 20220205392Abstract: A gas turbine engine is provided having a combustion section with a liner extending between a forward end and an aft end. A structural member is positioned in or around at least a portion of the combustion section. Additionally, a piston ring holder is provided attached to the structural member at a first end and positioned proximate to the aft end of the liner at a second end. The piston ring holder is a bimetallic member including a first portion formed of a first material and a second portion formed of a second material. A coefficient of thermal expansion of the first material is different than a coefficient of thermal expansion of the second material.Type: ApplicationFiled: October 15, 2021Publication date: June 30, 2022Inventors: Nicholas John Bloom, Michael Alan Stieg, Brian Christopher Towle
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Patent number: 11268697Abstract: Combustor assemblies for gas turbine engines are provided. For example, a combustor assembly comprises a combustor dome, a first heat shield having an edge, a second heat shield having an edge, and a seal extending from the edge of the first heat shield to the edge of the second heat shield such that the seal spans a gap between the first heat shield and the second heat shield. In another embodiment, the seal has a first contact portion contacting the edge of the first heat shield, a second contact portion contacting the edge of the second heat shield edge, and a connecting portion connecting the first portion and the second portion. The first contact portion and the second contact portion project away from the connecting portion. Methods for sealing between adjacent heat shields of a combustor assembly also are provided.Type: GrantFiled: August 12, 2019Date of Patent: March 8, 2022Assignee: General Electric CompanyInventors: Michael Alan Stieg, Valeria Proano Cadena, Aaron Michael Dziech, Michael Todd Radwanski, Donald Michael Corsmeier
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Patent number: 11149646Abstract: A gas turbine engine is provided having a combustion section with a liner extending between a forward end and an aft end. A structural member is positioned in or around at least a portion of the combustion section. Additionally, a piston ring holder is provided attached to the structural member at a first end and positioned proximate to the aft end of the liner at a second end. The piston ring holder is a bimetallic member including a first portion formed of a first material and a second portion formed of a second material. A coefficient of thermal expansion of the first material is different than a coefficient of thermal expansion of the second material.Type: GrantFiled: September 2, 2015Date of Patent: October 19, 2021Assignee: General Electric CompanyInventors: Nicholas John Bloom, Michael Alan Stieg, Brian Christopher Towle
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Publication number: 20210310657Abstract: A combustor assembly for a gas turbine engine includes an outer liner that at least partially defines a combustion chamber. The outer liner extends between an aft end and a forward end generally along an axial direction within an outer casing of the gas turbine engine. The outer liner includes an inner surface facing the combustion chamber and an outer surface facing away from the combustion chamber. The combustor assembly includes a radial damper assembly disposed against the outer liner at a plurality of circumferential points.Type: ApplicationFiled: February 4, 2021Publication date: October 7, 2021Inventors: Mark Willard Marusko, Michael Alan Stieg, Brian Christopher Towle
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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: 10935242Abstract: A gas turbine engine and combustor assembly is generally provided. The gas turbine engine may include an outer casing while the combustor assembly may include a liner and a damper assembly. The liner may at least partially define a combustion chamber extending between an aft end and a forward end generally along an axial direction within the outer casing. The liner may include an inner surface facing the combustion chamber and an outer surface facing away from the combustion chamber. The damper assembly may extend between the outer casing and the outer surface of the liner. The damper assembly may include a selectively separable support and damper spring. The damper spring may be disposed between the support and the liner.Type: GrantFiled: July 7, 2016Date of Patent: March 2, 2021Assignee: General Electric CompanyInventors: Mark Willard Marusko, Michael Alan Stieg, Brian Christopher Towle
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Publication number: 20200003418Abstract: Combustor assemblies for gas turbine engines are provided. For example, a combustor assembly comprises a combustor dome, a first heat shield having an edge, a second heat shield having an edge, and a seal extending from the edge of the first heat shield to the edge of the second heat shield such that the seal spans a gap between the first heat shield and the second heat shield. In another embodiment, the seal has a first contact portion contacting the edge of the first heat shield, a second contact portion contacting the edge of the second heat shield edge, and a connecting portion connecting the first portion and the second portion. The first contact portion and the second contact portion project away from the connecting portion. Methods for sealing between adjacent heat shields of a combustor assembly also are provided.Type: ApplicationFiled: August 12, 2019Publication date: January 2, 2020Inventors: Michael Alan Stieg, Valeria Proano Cadena, Aaron Michael Dziech, Michael Todd Radwanski, Donald Michael Corsmeier
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Patent number: 10401030Abstract: Components and methods for forming components are provided. For example, a method for forming a component includes laying up a plurality of plies to form a component preform that defines an axis of symmetry and a circumferential direction. Laying up the plurality of plies includes overlapping ends of the plurality of plies to define overlap regions and offsetting the overlap regions along the circumferential direction such that any radial line drawn from the axis of symmetry through the plies passes through only one overlap region. In another embodiment, a component includes a body that is symmetric about an axis of symmetry and that defines a circumferential direction and a radial direction. The body is formed from a plurality of plies and has a substantially uniform thickness. Ends of the plurality of plies are overlapped to define a plurality of overlap regions, which are offset along the circumferential direction.Type: GrantFiled: July 12, 2016Date of Patent: September 3, 2019Assignee: General Electric CompanyInventors: Michael Alan Stieg, Brian Christopher Towle, Darrell Glenn Senile, Gregory Scott Phelps, Jeffrey Douglas Johnson
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Patent number: 10378769Abstract: Combustor assemblies having heat shields heat shield attachment features are provided. For example, a combustor assembly includes a dome plate defining first and second apertures, and a heat shield defining first and second openings. The heat shield includes a first cup extending about the first opening and a second cup extending about the second opening. The combustor assembly further includes a collar having a first frame at least partially surrounding the first cup and a second frame at least partially surrounding the second cup. The collar includes a first fastening feature and the dome plate includes a second fastening feature. The first fastening feature mates with the second fastening feature to couple the heat shield to the dome plate. The combustor assembly also may include an attachment piece configured to couple the heat shield to the dome plate. Methods for forming ceramic matrix composite (CMC) heat shields also are provided.Type: GrantFiled: September 30, 2016Date of Patent: August 13, 2019Assignee: General Electric CompanyInventors: Michael Todd Radwanski, Michael Alan Stieg, Donald Michael Corsmeier
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Patent number: 10378772Abstract: Combustor assemblies for gas turbine engines are provided. For example, a combustor assembly comprises a combustor dome, a first heat shield having an edge, a second heat shield having an edge, and a seal extending from the edge of the first heat shield to the edge of the second heat shield such that the seal spans a gap between the first heat shield and the second heat shield. In another embodiment, the seal has a first contact portion contacting the edge of the first heat shield, a second contact portion contacting the edge of the second heat shield edge, and a connecting portion connecting the first portion and the second portion. The first contact portion and the second contact portion project away from the connecting portion. Methods for sealing between adjacent heat shields of a combustor assembly also are provided.Type: GrantFiled: January 19, 2017Date of Patent: August 13, 2019Assignee: General Electric CompanyInventors: Michael Alan Stieg, Valeria Proano Cadena, Aaron Michael Dziech, Michael Todd Radwanski, Donald Michael Corsmeier
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Publication number: 20190203940Abstract: A combustor assembly for a gas turbine engine includes a dome defining 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 is received within the slot of the dome. In one aspect, the forward end of the liner defines blind warming openings that allow a warming airflow to actively warm the forward end during transient operation of the engine. In another aspect, the dome defines a plurality of impingement openings that allow a warming airflow to impinge on the forward end to actively warm the liner during transient operation of the engine. In another aspect, a grommet coupling a pin with the liner defines a plurality of warming passages that allow a warming airflow to flow therethrough to warm the forward end of the liner during transient engine operation.Type: ApplicationFiled: January 3, 2018Publication date: July 4, 2019Inventors: Michael Alan Stieg, Nicholas John Bloom, Brett Joseph Geiser
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Publication number: 20190203939Abstract: A combustor assembly for a gas turbine engine includes a dome defining 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 is received within the slot of the dome. In one exemplary aspect, the combustor assembly includes features that warm the forward end of the liner during transient operation of the engine. Furthermore, the combustor assembly includes features that reduce the thermal gradient between the forward end and the other portions of the liner. In this way, improved durability of the liner may be achieved.Type: ApplicationFiled: January 3, 2018Publication date: July 4, 2019Inventors: Michael Alan Stieg, Nicholas John Bloom
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Publication number: 20190203611Abstract: A combustor assembly for a gas turbine engine includes a dome defining 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. At least a portion of the forward end is received within the slot of the dome. The forward end of the liner defines a plurality of warming holes that allow for a warming airflow to flow therethrough to warm the forward end at a faster rate during transient operating conditions of the engine thereby reducing transient stresses and increasing liner durability.Type: ApplicationFiled: January 3, 2018Publication date: July 4, 2019Inventors: Michael Alan Stieg, Nicholas John Bloom, Eric Ryan Newburn, Brett Joseph Geiser
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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