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公开(公告)号：US10816199B2
公开(公告)日：2020-10-27
申请号：US15417381
申请日：2017-01-27
Applicant: General Electric Company
Inventor： Donald Michael Corsmeier
Abstract: Combustor assemblies and combustor heat shields are provided. As one example, a combustor assembly comprises a flow path assembly including an outer wall, an inner wall, and a combustor dome that define a combustion chamber and are formed from a ceramic matrix composite (CMC) material. The combustor dome defines a plurality of dome openings, and a heat shield is positioned between the combustor dome and the combustion chamber that comprises a plurality of heat shield segments. Each heat shield segment defines a heat shield aperture that is aligned with a dome opening, and an aft surface of each segment is concave and a forward surface of each segment is convex. One of a plurality of fuel-air mixers is positioned through each heat shield aperture and dome opening, and one collar of a plurality of collars extends through each heat shield aperture to couple the heat shield to the fuel-air mixer.
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公开(公告)号：US20190003710A1
公开(公告)日：2019-01-03
申请号：US15417381
申请日：2017-01-27
Applicant: General Electric Company
Inventor： Donald Michael Corsmeier
Abstract: Combustor assemblies and combustor heat shields are provided. As one example, a combustor assembly comprises a flow path assembly including an outer wall, an inner wall, and a combustor dome that define a combustion chamber and are formed from a ceramic matrix composite (CMC) material. The combustor dome defines a plurality of dome openings, and a heat shield is positioned between the combustor dome and the combustion chamber that comprises a plurality of heat shield segments. Each heat shield segment defines a heat shield aperture that is aligned with a dome opening, and an aft surface of each segment is concave and a forward surface of each segment is convex. One of a plurality of fuel-air mixers is positioned through each heat shield aperture and dome opening, and one collar of a plurality of collars extends through each heat shield aperture to couple the heat shield to the fuel-air mixer.
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公开(公告)号：US09964309B2
公开(公告)日：2018-05-08
申请号：US14579267
申请日：2014-12-22
Applicant: General Electric Company
Inventor： Donald Michael Corsmeier , Mark Eugene Noe , Michael Todd Radwanski , Oliver Roghe , Jessica Licardi Subit , Ming Xie
CPC classification number: F23R3/42 , F23R3/002 , F23R3/007 , F23R2900/00017 , Y10T29/4932 , Y10T29/49826
Abstract: A combustor for a gas turbine engine is disclosed. The combustor is described as comprising a dome plate coupled to a liner thereof, with at least one heat shield comprised of a ceramic matrix composite coupled at the aft end of the dome plate. Also described is a method for assembling a combustor for a gas turbine engine, including releasing a metal alloy heat shield from a dome plate and providing a ceramic matrix composite heat shield as replacement.
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公开(公告)号：US20180094813A1
公开(公告)日：2018-04-05
申请号：US15281698
申请日：2016-09-30
Applicant: General Electric Company
Inventor： Donald Michael Corsmeier
IPC: F23R3/00
CPC classification number: F23R3/002 , F23R3/007 , F23R3/60 , F23R2900/00012
Abstract: Combustor assemblies having heat shields and features for attaching the heat shields are provided. For example, a combustor assembly includes a combustor dome defining an aperture, and a heat shield defining an opening and including a cup extending about the opening that extends toward the aperture of the combustor dome. The combustor assembly also includes a collar comprising a first piece and a second piece that each surround a portion of the heat shield cup. The collar may include a first arm, a second arm, and a body connecting the first and second arms such that the collar defines a recess between the first and second arms. The combustor assembly also may include an attachment piece with a flange that is positioned in the recess with a heat shield flange; the attachment piece attaches to the combustor dome to couple the heat shield and the combustor dome.
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公开(公告)号：US20180094812A1
公开(公告)日：2018-04-05
申请号：US15281673
申请日：2016-09-30
Applicant: General Electric Company
Inventor： Donald Michael Corsmeier
CPC classification number: F23R3/002 , F23R3/007 , F23R3/283 , F23R3/60 , F23R2900/00012
Abstract: Combustor assemblies are provided. For example, a combustor assembly includes a combustor liner defining a combustion chamber and an annular combustor dome positioned at a forward end of the combustor liner that defines a plurality of dome apertures. The combustor assembly further includes an annular heat shield positioned between the combustor dome and the combustion chamber, a plurality of adapters positioned forward of the heat shield, and a plurality of collars. The heat shield defines a plurality of heat shield apertures that are aligned with the dome apertures. One adapter is attached to the combustor dome at each dome aperture, and the adapters are. One collar extends through each heat shield aperture to couple the heat shield to the combustor dome. Further, ceramic matrix composite (CMC) heat shields are provided that may include an annular body defining a plurality of heat shield apertures, as well as inner and outer wings.
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Patent Agency Ranking
公开(公告)号：US11905843B2
公开(公告)日：2024-02-20
申请号：US16837553
申请日：2020-04-01
Applicant: General Electric Company
Inventor： Donald Michael Corsmeier , Bernard James Renggli , Kurt J. Bonner
CPC classification number: F01D25/30 , F01D25/005 , F01D25/14 , F05D2220/323 , F05D2240/14 , F05D2260/20 , F05D2260/31 , F05D2300/6033
Abstract: A liner support system for an exhaust liner in an aircraft engine. The liner support system includes a plurality of posts that space the exhaust liner from the exhaust duct, the plurality of posts spacing the exhaust liner from the exhaust duct further supporting the exhaust liner. Each post includes an interface region adjacent to the back side of the exhaust liner sealed to the back side of the exhaust liner, a shank extending to a low pressure region, and a hollow passageway internal to the shank, providing fluid communication between the interface region and the low pressure region. The low pressure region results in pressure against the liner, pulling the liner adjacent the post interface region against the post while preventing fluid leakage between the exhaust liner and the interface region. The posts create a pattern of alternating pressures in the liner allowing for elimination of hangers.
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公开(公告)号：US11420265B2
公开(公告)日：2022-08-23
申请号：US17062715
申请日：2020-10-05
Applicant: General Electric Company
Inventor： Donald Michael Corsmeier
Abstract: An apparatus for continuous powder-based additive manufacturing of a large annular object or multiple smaller objects simultaneously is described. The build unit(s) of the apparatus includes a powder delivery mechanism, a powder recoating mechanism and an irradiation beam directing mechanism. The build unit(s) is attached to a rotating mechanism such that the build unit(s) rotates around and above the annular powder bed during production. The rotating mechanism is supported onto a central tower, and both the rotating mechanism and the tower are concentric with the non-rotating annular powder bed. An additive manufacturing method using the apparatus involves repetitive and continuous cycles of at least simultaneously rotating the build unit(s) to deposit powder onto the powder bed and irradiating the powder to form a fused additive layer. The continuous additive manufacturing process may be further aided with a helical configuration of the powder bed build surface.
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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：US20190024988A1
公开(公告)日：2019-01-24
申请号：US15652678
申请日：2017-07-18
Applicant: General Electric Company
Inventor： Nicholas Allan Wilson , Donald Michael Corsmeier
Abstract: A header for a heat exchanger includes a first barrel and a second barrel stacked on top of each other and being separated by a septum which may include one or more apertures. The first barrel and the second barrel may define a first manifold and a second manifold, respectively, which may be in fluid communication via the apertures in the septum. An inlet manifold is in fluid communication with the first manifold and the second manifold for providing a flow of heated fluid, the heated fluid being distributed through the first manifold and the second manifold before passing through a plurality of heat exchange tubes that extend from each of the first manifold and the second manifold.
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