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公开(公告)号：US20190137101A1
公开(公告)日：2019-05-09
申请号：US16231103
申请日：2018-12-21
Applicant: General Electric Company
Inventor： Nicholas John Bloom , Daniel Kirtley , Michael Alan Stieg , Brian Christopher Towle , Chad Holden Sutton
Abstract: 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.
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公开(公告)号：US10041677B2
公开(公告)日：2018-08-07
申请号：US14972281
申请日：2015-12-17
Applicant: General Electric Company
Abstract: A combustion liner for use in a combustor assembly is provided. The combustion liner includes a side wall that defines a combustion chamber having a main flow axis extending therethrough. The combustion chamber channels a flow of combustion gas therethrough along a mixer swirl flow axis oriented obliquely relative to the main flow axis. The combustion liner also includes film cooling holes defined within the side wall. The film cooling holes are configured to discharge a pressurized fluid jet into the combustion chamber, and arranged in at least a first row and a second row positioned a first distance from the first row. The film cooling holes are arranged such that, when mixed with the flow of combustion gas, the pressurized fluid jet discharged from film cooling holes in the first row is directed along a discharge flow axis misaligned from film cooling holes in the second row.
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公开(公告)号：US20180202659A1
公开(公告)日：2018-07-19
申请号：US15409635
申请日：2017-01-19
Applicant: General Electric Company
Inventor： Michael Alan Stieg , Valeria Proano Cadena , Aaron Michael Dziech , Michael Todd Radwanski , Donald Michael Corsmeier
IPC: F23R3/00
CPC classification number: F23R3/007 , F05D2240/15 , F05D2240/35 , F05D2240/55 , F23R3/002 , F23R3/10 , F23R3/60 , F23R2900/00012 , F23R2900/00018
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：US20240219026A1
公开(公告)日：2024-07-04
申请号：US18432392
申请日：2024-02-05
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 including an outer casing, the gas turbine engine defining an axial direction, the combustor assembly includes a liner at least partially defining a combustion chamber extending between an aft end and a forward end generally along the axial direction within the outer casing, the liner including an inner surface facing the combustion chamber and an outer surface facing away from the combustion chamber, and a damper assembly extending between the outer casing and the outer surface of the liner, the damper assembly including a selectively separable support and a damper spring, the damper spring being disposed between the support and the liner.
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公开(公告)号：US20220333778A1
公开(公告)日：2022-10-20
申请号：US17855905
申请日：2022-07-01
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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Patent Agency Ranking
公开(公告)号：US20210063016A1
公开(公告)日：2021-03-04
申请号：US16654571
申请日：2019-10-16
Applicant: General Electric Company
Inventor： Michael Alan Stieg , Darrell Glenn Senile , Gregory Scott Phelps , Jeffrey Douglas Johnson , Chad Holden Sutton , Robert Andrew Stowers
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：US20200003418A1
公开(公告)日：2020-01-02
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：US10378772B2
公开(公告)日：2019-08-13
申请号：US15409635
申请日：2017-01-19
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：US10197278B2
公开(公告)日：2019-02-05
申请号：US14842883
申请日：2015-09-02
Applicant: General Electric Company
Inventor： Nicholas John Bloom , Daniel Kirtley , Michael Alan Stieg , Brian Christopher Towle , Chad Holden Sutton
Abstract: 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.
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公开(公告)号：US20180094811A1
公开(公告)日：2018-04-05
申请号：US15281553
申请日：2016-09-30
Applicant: General Electric Company
Inventor： Michael Todd Radwanski , Michael Alan Stieg , Donald Michael Corsmeier
IPC: F23R3/00
CPC classification number: F23R3/002 , F23R3/007 , F23R3/60 , F23R2900/00018
Abstract: 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.
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