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公开(公告)号：US20230059927A1
公开(公告)日：2023-02-23
申请号：US17979057
申请日：2022-11-02
Applicant: General Electric Company
Inventor： Christopher Ryan Johnson , Paul Hadley Vitt , Eric Joseph Schroeder , Carlos Gilberto Fernandez-Soto
IPC: F02C7/24
Abstract: A turbine engine and method of operating includes an engine core with a compressor, a combustor, and a turbine in axial flow arrangement. A flow path extends through the engine core from the compressor to the turbine to define a flow direction for a working airflow through the engine core.
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公开(公告)号：US10253648B2
公开(公告)日：2019-04-09
申请号：US15060876
申请日：2016-03-04
Applicant: General Electric Company
Inventor： David Todd Bentley , Christopher Ryan Johnson , Brandon Flowers Powell
Abstract: The present disclosure is directed to a variable area turbine nozzle. The variable area turbine nozzle includes a first vane segment, a second vane segment arranged with the first vane segment, and a trailing edge segment arranged with the first and second vane segments. The vane also includes a first actuating system for pivoting the second vane segment with respect to the first vane segment and a second actuating system for pivoting the trailing edge with respect to the first and second vane segments.
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公开(公告)号：US11519333B2
公开(公告)日：2022-12-06
申请号：US17016670
申请日：2020-09-10
Applicant: General Electric Company
Inventor： Christopher Ryan Johnson , Paul Hadley Vitt , Eric Joseph Schroeder , Carlos Gilberto Fernandez-Soto
IPC: F02C7/24
Abstract: Aspects of the disclosure generally relate to a turbine engine and method of operating a turbine engine having an engine core including a compressor, combustor, and turbine in axial flow arrangement, whereby a working airflow passes through the engine core from the compressor to the turbine to define a flow direction through the engine core. The method includes generating a shockwave in the working airflow that propagates in the flow direction, and at least partially attenuating the shockwave.
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Patent Agency Ranking
公开(公告)号：US20170138202A1
公开(公告)日：2017-05-18
申请号：US14941706
申请日：2015-11-16
Applicant: General Electric Company
Inventor： Aspi Rustom Wadia , Lyle Douglas Dailey , Christopher Ryan Johnson , Daniel Mollmann
CPC classification number: F01D5/141 , F01D9/041 , F05D2220/32 , F05D2240/125 , F05D2240/307 , Y02T50/672 , Y02T50/673
Abstract: Turbine assemblies for gas turbine engines are provided. In one embodiment, a turbine assembly includes a row of circumferentially adjacent turbine rotor blades, each blade in the row of blades including an airfoil defining a chord extending axially between opposite leading and trailing edges of the airfoil. The chords in a mid-span region of each blade are shorter than the chords in span regions adjacent to the blade root and the blade tip. In another exemplary embodiment, a turbine assembly includes a row of circumferentially adjacent turbine stator vanes, each vane in the row of vanes including an airfoil defining a chord extending axially between opposite leading and trailing edges of the airfoil. The chords in a mid-span region of each vane are shorter than the chords in span regions adjacent to the vane root and the vane tip. A turbine rotor blade for a gas turbine engine also is provided.
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公开(公告)号：US20240247614A1
公开(公告)日：2024-07-25
申请号：US18625749
申请日：2024-04-03
Applicant: General Electric Company
Inventor： Christopher Ryan Johnson , Paul Hadley Vitt , Eric Joseph Schroeder , Carlos Gilberto Fernandez-Soto
IPC: F02C7/24
CPC classification number: F02C7/24
Abstract: A turbine engine and method of operating includes an engine core with a compressor, a combustor, and a turbine in axial flow arrangement. A flow path extends through the engine core from the compressor to the turbine to define a flow direction for a working airflow through the engine core.
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公开(公告)号：US11970979B2
公开(公告)日：2024-04-30
申请号：US17979057
申请日：2022-11-02
Applicant: General Electric Company
Inventor： Christopher Ryan Johnson , Paul Hadley Vitt , Eric Joseph Schroeder , Carlos Gilberto Fernandez-Soto
IPC: F02C7/24
CPC classification number: F02C7/24
Abstract: A turbine engine and method of operating includes an engine core with a compressor, a combustor, and a turbine in axial flow arrangement. A flow path extends through the engine core from the compressor to the turbine to define a flow direction for a working airflow through the engine core.
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公开(公告)号：US20220074348A1
公开(公告)日：2022-03-10
申请号：US17016670
申请日：2020-09-10
Applicant: General Electric Company
Inventor： Christopher Ryan Johnson , Paul Hadley Vitt , Eric Joseph Schroeder , Carlos Gilberto Fernandez-Soto
IPC: F02C7/24
Abstract: Aspects of the disclosure generally relate to a turbine engine and method of operating a turbine engine having an engine core including a compressor, combustor, and turbine in axial flow arrangement, whereby a working airflow passes through the engine core from the compressor to the turbine to define a flow direction through the engine core. The method includes generating a shockwave in the working airflow that propagates in the flow direction, and at least partially attenuating the shockwave.
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公开(公告)号：US20170254215A1
公开(公告)日：2017-09-07
申请号：US15060876
申请日：2016-03-04
Applicant: General Electric Company
Inventor： David Todd Bentley , Christopher Ryan Johnson , Brandon Flowers Powell
CPC classification number: F01D17/162 , F01D9/041 , F01D17/085 , F05D2220/32 , F05D2240/122 , F05D2240/124 , F05D2240/128 , F05D2270/303 , F05D2270/66 , Y02T50/673
Abstract: The present disclosure is directed to a variable area turbine nozzle. The variable area turbine nozzle includes a first vane segment, a second vane segment arranged with the first vane segment, and a trailing edge segment arranged with the first and second vane segments. The vane also includes a first actuating system for pivoting the second vane segment with respect to the first vane segment and a second actuating system for pivoting the trailing edge with respect to the first and second vane segments.
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