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公开(公告)号：US11149646B2
公开(公告)日：2021-10-19
申请号：US14842954
申请日：2015-09-02
Applicant: General Electric Company
Inventor： Nicholas John Bloom , Michael Alan Stieg , Brian Christopher Towle
Abstract: 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.
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公开(公告)号：US10935242B2
公开(公告)日：2021-03-02
申请号：US15203914
申请日：2016-07-07
Applicant: General Electric Company
Inventor： Mark Willard Marusko , Michael Alan Stieg , Brian Christopher Towle
Abstract: 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.
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公开(公告)号：US10401030B2
公开(公告)日：2019-09-03
申请号：US15207814
申请日：2016-07-12
Applicant: General Electric Company
Inventor： Michael Alan Stieg , Brian Christopher Towle , Darrell Glenn Senile , Gregory Scott Phelps , Jeffrey Douglas Johnson
Abstract: 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.
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公开(公告)号：US20180051880A1
公开(公告)日：2018-02-22
申请号：US15239888
申请日：2016-08-18
Applicant: General Electric Company
Inventor： Michael Alan Stieg , Darrell Glenn Senile , Gregory Scott Phelps , Jeffrey Douglas Johnson , Chad Holden Sutton , Robert Andrew Stowers
IPC: F23R3/00
CPC classification number: F23R3/002 , F23R3/007 , F23R3/60 , F23R2900/00005 , F23R2900/00017 , F23R2900/00018
Abstract: 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.
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公开(公告)号：US20170058778A1
公开(公告)日：2017-03-02
申请号：US14842954
申请日：2015-09-02
Applicant: General Electric Company
Inventor： Nicholas John Bloom , Michael Alan Stieg , Brian Christopher Towle
Abstract: 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.
Abstract translation: 提供一种燃气涡轮发动机，其具有燃烧部分，其具有在前端和后端之间延伸的衬套。 结构构件定位在燃烧部分的至少一部分中或周围。 此外，活塞环保持器在第一端处被附接到结构构件并且在第二端处靠近衬套的后端定位。 活塞环保持器是双金属构件，其包括由第一材料形成的第一部分和由第二材料形成的第二部分。 第一材料的热膨胀系数不同于第二材料的热膨胀系数。
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Patent Agency Ranking
公开(公告)号：US11920789B2
公开(公告)日：2024-03-05
申请号：US17167165
申请日：2021-02-04
Applicant: General Electric Company
Inventor： Mark Willard Marusko , Michael Alan Stieg , Brian Christopher Towle
CPC classification number: F23R3/002 , F23R3/007 , F23R3/50 , F23R3/60 , F23R2900/00014
Abstract: 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.
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公开(公告)号：US11898494B2
公开(公告)日：2024-02-13
申请号：US17502502
申请日：2021-10-15
Applicant: General Electric Company
Inventor： Nicholas John Bloom , Michael Alan Stieg , Brian Christopher Towle
Abstract: 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.
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公开(公告)号：US11268697B2
公开(公告)日：2022-03-08
申请号：US16537836
申请日：2019-08-12
Applicant: General Electric Company
Inventor： Michael Alan Stieg , Valeria Proano Cadena , Aaron Michael Dziech , Michael Todd Radwanski , Donald Michael Corsmeier
Abstract: 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.
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公开(公告)号：US20190203940A1
公开(公告)日：2019-07-04
申请号：US15860835
申请日：2018-01-03
Applicant: General Electric Company
Inventor： Michael Alan Stieg , Nicholas John Bloom , Brett Joseph Geiser
CPC classification number: F23R3/04 , F23R3/007 , F23R2900/00005 , F23R2900/03044
Abstract: 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.
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公开(公告)号：US20190203939A1
公开(公告)日：2019-07-04
申请号：US15860820
申请日：2018-01-03
Applicant: General Electric Company
Inventor： Michael Alan Stieg , Nicholas John Bloom
Abstract: 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.
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