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公开(公告)号：US20220228744A1
公开(公告)日：2022-07-21
申请号：US17680751
申请日：2022-02-25
Applicant: General Electric Company
Inventor： Brandon ALlanson Reynolds , Matthew Mark Weaver , Daniel Patrick Kerns
Abstract: Combustor dome assemblies having combustor deflectors are provided. For example, a combustor dome assembly comprises a combustor dome defining an opening; a ceramic matrix composite (CMC) deflector positioned adjacent the combustor dome on an aft side of the assembly; a fuel-air mixer defining a groove about an outer perimeter thereof; and a seal plate including a key. The CMC deflector includes a cup extending forward through the opening in the combustor dome that defines one or more bayonets and a slot. The bayonets are received in the fuel-air mixer groove, and the seal plate key is received in the CMC deflector slot. In another embodiment, where the seal plate may be omitted, a spring is positioned between the fuel-air mixer and the CMC deflector to hold the CMC deflector in place with respect to the combustor dome. Methods of assembling combustor dome assemblies having CMC deflectors also are provided.
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公开(公告)号：US20190338676A1
公开(公告)日：2019-11-07
申请号：US16454975
申请日：2019-06-27
Applicant: General Electric Company
Inventor： Daniel Patrick Kerns , Mark Eugene Noe , Dennis Paul Dry , Brandon ALlanson Reynolds
Abstract: A flow path assembly for a gas turbine engine is provided. The flow path assembly may include an outer casing comprising a metal material having a first coefficient of thermal expansion, a ceramic structure comprising a ceramic material having a second coefficient of thermal expansion, and a mounting component attached on a first end to the outer casing and attached on a second end to the ceramic structure. The mounting component may be constructed from at least two materials transitioning from the first end to the second end such that the coefficient of thermal expansion is different at the first end than the second end.
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公开(公告)号：US10371383B2
公开(公告)日：2019-08-06
申请号：US15417602
申请日：2017-01-27
Applicant: General Electric Company
Inventor： Brandon ALlanson Reynolds , Jonathan David Baldiga , Andrew Scott Bilse , Michael Todd Radwanski , Ernesto Andres Vallejo Ruiz , Aaron Michael Dziech , Mark Eugene Noe
Abstract: Flow path assemblies and gas turbine engines are provided. A flow path assembly may comprise a combustor dome positioned at a forward end of a combustor of a combustion section of a gas turbine engine, and a unitary outer wall including a combustor portion extending through the combustion section and a turbine portion extending through at least a first turbine stage of a turbine section of the gas turbine engine. The combustor portion and the turbine portion are integrally formed as a single unitary structure. The flow path assembly also comprises an inner wall extending from the forward end of the combustor through at least the combustion section. The combustor dome extends radially from the unitary outer wall to the inner wall and is configured to move axially with respect to the inner wall and the unitary outer wall. Other flow path assemblies and gas turbine engine configurations are provided.
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公开(公告)号：US20180266264A1
公开(公告)日：2018-09-20
申请号：US15426354
申请日：2017-02-07
Applicant: General Electric Company
Inventor： Daniel Patrick Kerns , Brandon ALlanson Reynolds
CPC classification number: F01D11/04 , F01D9/023 , F01D9/041 , F01D9/042 , F01D11/005 , F01D25/005 , F01D25/12 , F02C3/14 , F05D2220/32 , F05D2240/35 , F05D2260/20 , F05D2300/6033 , F23R3/002 , F23R3/50 , F23R3/60 , F23R2900/00018 , Y02T50/672 , Y02T50/673 , Y02T50/675
Abstract: Flow path assemblies for gas turbine engines are provided. For example, a flow path assembly comprises an inner wall defining an inner boundary of a flow path and a plurality of pockets therein, and a unitary outer wall defining an outer boundary of the flow path. The unitary outer wall includes combustor and turbine portions that are integrally formed as a single unitary structure. The flow path assembly further comprises a plurality of nozzle airfoils that each have an inner end radially opposite an outer end and define an internal cavity for receipt of a flow of cooling fluid. The inner end of each nozzle airfoil is received in one of the plurality of inner wall pockets and defines an outlet for the flow of cooling fluid to flow from the internal cavity to the pocket, which forms a fluid curtain to discourage fluid leakage from the flow path.
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公开(公告)号：US20240117756A1
公开(公告)日：2024-04-11
申请号：US18363797
申请日：2023-08-02
Applicant: General Electric Company
Inventor： Daniel Patrick Kerns , Mark Eugene Noe , Dennis Paul Dry , Brandon ALlanson Reynolds
CPC classification number: F01D25/246 , F01D25/28 , F23R3/002 , F23R3/50 , F23R3/60 , F05D2220/32 , F05D2240/35 , F05D2300/177 , F05D2300/50212 , F05D2300/6033 , F23R2900/00018
Abstract: A flow path assembly for a gas turbine engine is provided. The flow path assembly may include an outer casing comprising a metal material having a first coefficient of thermal expansion, a ceramic structure comprising a ceramic material having a second coefficient of thermal expansion, and a mounting component attached on a first end to the outer casing and attached on a second end to the ceramic structure. The mounting component may be constructed from at least two materials transitioning from the first end to the second end such that the coefficient of thermal expansion is different at the first end than the second end.
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Patent Agency Ranking
公开(公告)号：US11441436B2
公开(公告)日：2022-09-13
申请号：US16994751
申请日：2020-08-17
Applicant: General Electric Company
IPC: F01D9/04 , F01D11/00 , F01D25/00 , F01D25/24 , C04B35/573 , C04B37/00 , C04B35/571 , C04B35/515 , C04B35/80
Abstract: Flow path assemblies and methods for forming such flow path assemblies for gas turbine engines are provided. For example, a flow path assembly for a gas turbine engine has a boundary structure, an airfoil, and a locking feature. The boundary structure and the airfoil are formed from a composite material. The boundary structure defines an opening and a cutout proximate the opening, and the airfoil is sized to fit within the opening of the boundary structure. The locking feature is received within the cutout defined by the boundary structure to interlock the airfoil with the boundary structure.
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公开(公告)号：US10385731B2
公开(公告)日：2019-08-20
申请号：US15620134
申请日：2017-06-12
Applicant: General Electric Company
Inventor： Daniel Patrick Kerns , Mark Eugene Noe , Dennis Paul Dry , Brandon ALlanson Reynolds
Abstract: A flow path assembly for a gas turbine engine is provided. The flow path assembly may include an outer casing comprising a metal material having a first coefficient of thermal expansion, a ceramic structure comprising a ceramic material having a second coefficient of thermal expansion, and a mounting component attached on a first end to the outer casing and attached on a second end to the ceramic structure. The mounting component may be constructed from at least two materials transitioning from the first end to the second end such that the coefficient of thermal expansion is different at the first end than the second end.
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公开(公告)号：US20190249556A1
公开(公告)日：2019-08-15
申请号：US16391507
申请日：2019-04-23
Applicant: General Electric Company
Inventor： Brandon ALlanson Reynolds , Jonathan David Baldiga , Darrell Glenn Senile , Daniel Patrick Kerns , Michael Ray Tuertscher , Aaron Michael Dziech , Brett Joseph Geiser
CPC classification number: F01D9/044 , F01D5/282 , F01D5/284 , F01D9/023 , F01D11/005 , F01D25/24 , F05D2300/6033 , F23R3/14 , F23R3/16 , F23R3/346 , F23R3/60 , F23R2900/00017 , F23R2900/00018
Abstract: Flow path assemblies having features for positioning the assemblies within a gas turbine engine are provided. For example, a flow path assembly comprises an inner wall and a unitary outer wall that includes an integral combustion portion and turbine portion, the combustor portion extending through a combustion section of the gas turbine engine and the turbine portion extending through at least a first turbine stage of a turbine section of the gas turbine engine. The flow path assembly further comprises at least two positioning members for radially centering the flow path assembly within the gas turbine engine. The positioning members extend to the flow path assembly from one or more structures external to the flow path assembly, constrain the flow path assembly tangentially, and allow radial and axial movement of the flow path assembly. Other embodiments for positioning flow path assemblies also are provided.
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9.发明授权公开(公告)号：US10247019B2
公开(公告)日：2019-04-02
申请号：US15440235
申请日：2017-02-23
Applicant: General Electric Company
Abstract: Flow path assemblies and methods for assembling a flow path assembly of a gas turbine engine are provided. For example, a flow path assembly comprises a unitary outer wall including combustor and turbine portions that are integrally formed as a single unitary structure; a single piece, generally annular inner band; and a plurality of nozzle airfoils extending from the unitary outer wall to the inner band. Each nozzle airfoil interfaces with the inner band to position the inner band within the assembly. An exemplary assembly method comprises inserting an inner band into a flow path having a unitary outer wall as its outer boundary; inserting a plurality of nozzle airfoils into the flow path; and securing the nozzle airfoils with respect to the unitary outer wall. The inner band interfaces with an inner end of each nozzle airfoil to radially locate the inner band within the flow path.
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公开(公告)号：US20180216822A1
公开(公告)日：2018-08-02
申请号：US15417399
申请日：2017-01-27
Applicant: General Electric Company
Inventor： Mark Eugene Noe , Shawn Michael Pearson , Joshua Tyler Mook , Brandon ALlanson Reynolds , Jonathan David Baldiga
CPC classification number: F23R3/002 , F01D5/06 , F01D5/225 , F01D9/023 , F01D9/04 , F01D25/246 , F02C3/14 , F02C7/22 , F05D2220/32 , F05D2230/53 , F05D2240/35 , F05D2300/6033 , F23R2900/00018 , Y02T50/672
Abstract: Gas turbine engines, as well as outer walls and flow path assemblies of gas turbine engines, are provided. For example, an outer wall of a flow path comprises a combustor portion extending through a combustion section, and a turbine portion extending through at least a first turbine stage of a turbine section. The combustor and turbine portions are integrally formed as a single unitary structure that defines an outer boundary of the flow path. As another example, a flow path assembly comprises a combustor dome positioned a forward end of a combustor; an outer wall extending from the combustor dome through at least a first turbine stage; and an inner wall extending from the combustor dome through at least a combustion section. The combustor dome extends radially from the outer wall to the inner wall and is integrally formed with the outer and inner walls as a single unitary structure.
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