-
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.
-
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.
-
公开(公告)号：US10253637B2
公开(公告)日：2019-04-09
申请号：US14967069
申请日：2015-12-11
Applicant: General Electric Company
Inventor： Eric Joseph Schroeder , Paul Hadley Vitt , Timothy John Swenson , Kirk Douglas Gallier , Aspi Rustom Wadia
Abstract: A turbine blade is described herein, the turbine blade including a blade root, a blade tip, and an airfoil extending between the blade root and the blade tip. The airfoil has opposite pressure and suction sides extending between a forward leading edge and an aft trailing edge of the airfoil, and a maximum thickness located between the leading edge and the trailing edge. The blade tip includes a winglet extending laterally outward from at least one of the pressure side and the suction side from a leading point between the leading edge and the maximum thickness aftward to a trailing point between the maximum thickness and the trailing edge.
-
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.
-
Patent Agency Ranking
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.
-
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.
-
公开(公告)号：US10934858B2
公开(公告)日：2021-03-02
申请号：US16365105
申请日：2019-03-26
Applicant: General Electric Company
Inventor： Eric Joseph Schroeder , Paul Hadley Vitt , Timothy John Swenson , Kirk Douglas Gallier , Aspi Rustom Wadia
Abstract: A turbine blade is described herein, the turbine blade including a blade root, a blade tip, and an airfoil extending between the blade root and the blade tip. The airfoil has opposite pressure and suction sides extending between a forward leading edge and an aft trailing edge of the airfoil, and a maximum thickness located between the leading edge and the trailing edge. The blade tip includes a winglet extending laterally outward from at least one of the pressure side and the suction side from a leading point between the leading edge and the maximum thickness aftward to a trailing point between the maximum thickness and the trailing edge.
-
公开(公告)号：US20190218918A1
公开(公告)日：2019-07-18
申请号：US16365105
申请日：2019-03-26
Applicant: General Electric Company
Inventor： Eric Joseph Schroeder , Paul Hadley Vitt , Timothy John Swenson , Kirk Douglas Gallier , Aspi Rustom Wadia
CPC classification number: F01D5/20 , F01D5/141 , F01D5/145 , F01D5/147 , F01D5/187 , F01D9/04 , F02C3/06 , F02C7/18 , F05D2220/36 , F05D2230/10 , F05D2240/307 , F05D2240/35 , F05D2260/20 , Y02T50/673 , Y02T50/676
Abstract: A turbine blade is described herein, the turbine blade including a blade root, a blade tip, and an airfoil extending between the blade root and the blade tip. The airfoil has opposite pressure and suction sides extending between a forward leading edge and an aft trailing edge of the airfoil, and a maximum thickness located between the leading edge and the trailing edge. The blade tip includes a winglet extending laterally outward from at least one of the pressure side and the suction side from a leading point between the leading edge and the maximum thickness aftward to a trailing point between the maximum thickness and the trailing edge.
-
公开(公告)号：US20170167275A1
公开(公告)日：2017-06-15
申请号：US14967069
申请日：2015-12-11
Applicant: General Electric Company
Inventor： Eric Joseph Schroeder , Paul Hadley Vitt , Timothy John Swenson , Kirk Douglas Gallier , Aspi Rustom Wadia
CPC classification number: F01D5/20 , F01D5/141 , F01D5/145 , F01D5/147 , F01D5/187 , F01D9/04 , F02C3/06 , F02C7/18 , F05D2220/36 , F05D2230/10 , F05D2240/307 , F05D2240/35 , F05D2260/20 , Y02T50/673 , Y02T50/676
Abstract: A turbine blade is described herein, the turbine blade including a blade root, a blade tip, and an airfoil extending between the blade root and the blade tip. The airfoil has opposite pressure and suction sides extending between a forward leading edge and an aft trailing edge of the airfoil, and a maximum thickness located between the leading edge and the trailing edge. The blade tip includes a winglet extending laterally outward from at least one of the pressure side and the suction side from a leading point between the leading edge and the maximum thickness aftward to a trailing point between the maximum thickness and the trailing edge.
-
-
-
-
-
-
-
-
Search Results
9
records
(took 0.017 seconds)
