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1.发明授权公开(公告)号：US11384651B2
公开(公告)日：2022-07-12
申请号：US16371362
申请日：2019-04-01
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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Patent Agency Ranking
公开(公告)号：US10774008B2
公开(公告)日：2020-09-15
申请号：US15710954
申请日：2017-09-21
Applicant: General Electric Company
Inventor： Suresh Subramanian , Mark Eugene Noe , James Dale Steibel , Jason David Shapiro , Brandon ALIanson Reynolds , Kurtis C. Montgomery , Jared Hogg Weaver , Daniel Gene Dunn
IPC: C04B37/00 , C04B35/80 , C04B35/657 , C04B35/628 , F02K9/97 , F01D11/08 , F01D25/00 , F01D5/28 , F23R3/00 , C04B35/573 , F01D9/04 , F02K1/82 , B32B18/00
Abstract: A ceramic matrix composite article includes a chemical vapor infiltration ceramic matrix composite base portion including ceramic fiber reinforcement material in a ceramic matrix material having between 0% and 5% free silicon. The ceramic matrix composite article further includes a melt infiltration ceramic matrix composite covering portion including a ceramic fiber reinforcement material in a ceramic matrix material having a greater percentage of free silicon than the chemical vapor infiltration ceramic matrix composite base portion.
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公开(公告)号：US20200025009A1
公开(公告)日：2020-01-23
申请号：US16377413
申请日：2019-04-08
Applicant: General Electric Company
Inventor： Daniel Patrick Kerns , Brandon ALIanson Reynolds
IPC: F01D11/04 , F01D9/04 , F01D25/12 , F01D25/00 , F02C3/14 , F01D9/02 , F23R3/00 , F23R3/50 , F01D11/00 , F23R3/60
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：US11149569B2
公开(公告)日：2021-10-19
申请号：US16390490
申请日：2019-04-22
Applicant: General Electric Company
Inventor： Brandon ALIanson Reynolds , Jonathan David Baldiga , Darrell Glenn Senile , Daniel Patrick Kerns , Michael Ray Tuertscher
Abstract: Flow path assemblies of gas turbine engines are provided. For example, a flow path assembly comprises an inner wall and a unitary outer wall that includes a combustor portion extending through a combustion section of the gas turbine engine 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 further comprises a plurality of nozzle airfoils, each nozzle airfoil having an inner end radially opposite an outer end. The inner wall or the unitary outer wall defines a plurality of openings therethrough, and each opening is configured for receipt of one of the plurality of nozzle airfoils. Methods of assembling flow path assemblies also are provided.
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公开(公告)号：US20200024999A1
公开(公告)日：2020-01-23
申请号：US16390490
申请日：2019-04-22
Applicant: General Electric Company
Inventor： Brandon ALIanson Reynolds , Jonathan David Baldiga , Darrell Glenn Senile , Daniel Patrick Kerns , Michael Ray Tuertscher
Abstract: Flow path assemblies of gas turbine engines are provided. For example, a flow path assembly comprises an inner wall and a unitary outer wall that includes a combustor portion extending through a combustion section of the gas turbine engine 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 further comprises a plurality of nozzle airfoils, each nozzle airfoil having an inner end radially opposite an outer end. The inner wall or the unitary outer wall defines a plurality of openings therethrough, and each opening is configured for receipt of one of the plurality of nozzle airfoils. Methods of assembling flow path assemblies also are provided.
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6.发明申请公开(公告)号：US20190226349A1
公开(公告)日：2019-07-25
申请号：US16371362
申请日：2019-04-01
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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