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公开(公告)号：US20230399951A1
公开(公告)日：2023-12-14
申请号：US17835091
申请日：2022-06-08
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Rathakrishnan Bhaskaran , Thomas W. Vandeputte
CPC classification number: F01D5/189 , F01D5/12 , F01D5/141 , F01D25/12 , F05D2220/323 , F05D2260/202 , F05D2240/304 , F05D2240/303 , F05D2240/35
Abstract: A turbine engine includes a compressor section, a combustion section, and a turbine section. Fuel combusted in the combustion section drive stages of airfoils in the turbine section to drive the compressor section. The airfoils can include a geometry near or at the trailing edge with a linear portion provided between the pressure side and a first curved portion, to reduce shock generated in the wake of the airfoils.
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Patent Agency Ranking
公开(公告)号：US20210147065A1
公开(公告)日：2021-05-20
申请号：US17108431
申请日：2020-12-01
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Trevor Howard Wood , Kishore Ramakrishnan , Davide Giacché , Angela Knepper , Nicholas Bown , Rathakrishnan Bhaskaran
Abstract: An aircraft assembly includes an engine, and intake, and a propeller assembly. The engine is mounted to at least one of a wing or fuselage of an aircraft. The intake is configured to provide air to the engine. The intake includes a body having an engine inlet through which air enters the intake. The propeller assembly includes propeller blades coupled to and driven by the engine. The propeller assembly is spaced an axial distance from the inlet opening of the intake wherein air passing by the propeller blades enters the intake. The propeller assembly has a propeller configuration that is at least one of sized or shaped to optimize performance of the propeller assembly based on an interaction between the propeller assembly and the intake.
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公开(公告)号：US11040767B2
公开(公告)日：2021-06-22
申请号：US15860280
申请日：2018-01-02
Applicant: General Electric Company
Inventor： Trevor Howard Wood , Kishore Ramakrishnan , Davide Giacché , Angela Knepper , Nicholas Bown , Rathakrishnan Bhaskaran
Abstract: An aircraft assembly includes an engine, and intake, and a propeller assembly. The engine is mounted to at least one of a wing or fuselage of an aircraft. The intake is configured to provide air to the engine. The intake includes a body having an engine inlet through which air enters the intake. The propeller assembly includes propeller blades coupled to and driven by the engine. The propeller assembly is spaced an axial distance from the inlet opening of the intake wherein air passing by the propeller blades enters the intake. The propeller assembly has a propeller configuration that is at least one of sized or shaped to optimize performance of the propeller assembly based on an interaction between the propeller assembly and the intake.
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公开(公告)号：US12084166B2
公开(公告)日：2024-09-10
申请号：US17108431
申请日：2020-12-01
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Trevor Howard Wood , Kishore Ramakrishnan , Davide Giacché , Angela Knepper , Nicholas Bown , Rathakrishnan Bhaskaran
CPC classification number: B64C11/18 , B64C11/14 , B64D33/02 , B64D2033/0293 , F02C7/04 , F05D2220/323
Abstract: An aircraft assembly includes an engine, and intake, and a propeller assembly. The engine is mounted to at least one of a wing or fuselage of an aircraft. The intake is configured to provide air to the engine. The intake includes a body having an engine inlet through which air enters the intake. The propeller assembly includes propeller blades coupled to and driven by the engine. The propeller assembly is spaced an axial distance from the inlet opening of the intake wherein air passing by the propeller blades enters the intake. The propeller assembly has a propeller configuration that is at least one of sized or shaped to optimize performance of the propeller assembly based on an interaction between the propeller assembly and the intake.
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公开(公告)号：US11840939B1
公开(公告)日：2023-12-12
申请号：US17835091
申请日：2022-06-08
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Rathakrishnan Bhaskaran , Thomas W. Vandeputte
CPC classification number: F01D5/141 , F01D5/189 , F04D29/324 , F04D29/384 , F04D29/544 , F05D2220/323 , F05D2240/303 , F05D2240/304 , F05D2260/202
Abstract: A turbine engine includes a compressor section, a combustion section, and a turbine section. Fuel combusted in the combustion section drive stages of airfoils in the turbine section to drive the compressor section. The airfoils can include a geometry near or at the trailing edge with a linear portion provided between the pressure side and a first curved portion, to reduce shock generated in the wake of the airfoils.
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公开(公告)号：US20190161167A1
公开(公告)日：2019-05-30
申请号：US15860280
申请日：2018-01-02
Applicant: General Electric Company
Inventor： Trevor Howard Wood , Kishore Ramakrishnan , Davide Giacché , Angela Knepper , Nicholas Bown , Rathakrishnan Bhaskaran
Abstract: An aircraft assembly includes an engine, and intake, and a propeller assembly. The engine is mounted to at least one of a wing or fuselage of an aircraft. The intake is configured to provide air to the engine. The intake includes a body having an engine inlet through which air enters the intake. The propeller assembly includes propeller blades coupled to and driven by the engine. The propeller assembly is spaced an axial distance from the inlet opening of the intake wherein air passing by the propeller blades enters the intake. The propeller assembly has a propeller configuration that is at least one of sized or shaped to optimize performance of the propeller assembly based on an interaction between the propeller assembly and the intake.
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