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Patent Agency Ranking
公开(公告)号：US10724376B2
公开(公告)日：2020-07-28
申请号：US15891401
申请日：2018-02-08
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Nicholas Joseph Kray , Nitesh Jain , Nagashiresha Gontla , Narendra Digamber Joshi , Paul Gerard Marsland , Wayne Allen Spence
Abstract: A blade and a turbomachine engine having the blade are disclosed. The blade includes an airfoil having a root portion, a tip portion, and a plurality of fins integrally coupled to the root portion. The plurality of fins is disposed along a thickness of the airfoil.
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公开(公告)号：US12168960B2
公开(公告)日：2024-12-17
申请号：US18357349
申请日：2023-07-24
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Nagashiresha Gontla
Abstract: A method of operating an engine is provided. The method includes operating the engine at a takeoff power level. Operating the engine at the takeoff power level includes operating the engine with a power performance indicator quantity (PIQPower) in a range of 1400 pounds per square inch (lbs/in2) to 2500 lbs/in2, wherein the power performance indicator quantity is determined according to: PIQ Power = PIQ HPTI PIQ HPCE × N 1 N 2 × Fn Total A HPCE .
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公开(公告)号：US20240384687A1
公开(公告)日：2024-11-21
申请号：US18357349
申请日：2023-07-24
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Nagashiresha Gontla
Abstract: A method of operating an engine is provided. The method includes operating the engine at a takeoff power level. Operating the engine at the takeoff power level includes operating the engine with a power performance indicator quantity (PIQPower) in a range of 1400 pounds per square inch (lbs/in2) to 2500 lbs/in2, wherein the power performance indicator quantity is determined according to: PIQ Power = PIQ HPTI PIQ HPCE × N 1 N 2 × Fn Total A HPCE .
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公开(公告)号：US20230184175A1
公开(公告)日：2023-06-15
申请号：US17587466
申请日：2022-01-28
Applicant: General Electric Company
Inventor： Nagashiresha Gontla , Ravindra Shankar Ganiger
IPC: F02C9/00
CPC classification number: F02C9/00 , F05D2260/4031 , F05D2220/32 , F05D2270/00
Abstract: A gas turbine engine includes a turbomachine having a compressor, a combustor, and a turbine in serial flow order. The turbomachine includes a low pressure shaft, a gearbox, a motor, a fan shaft, and a compressor forward frame. The low pressure shaft is configured to be driven by the turbine and is configured to drive the gearbox. The motor is also configured to drive the gearbox. The gearbox is configured to drive the fan shaft. A connection is provided between the compressor forward frame and at least one of the motor and the gearbox.
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公开(公告)号：US20200149399A1
公开(公告)日：2020-05-14
申请号：US15891401
申请日：2018-02-08
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Nicholas Joseph Kray , Nitesh Jain , Nagashiresha Gontla , Narendra Digamber Joshi , Paul Gerard Marsland , Wayne Allen Spence
Abstract: A blade and a turbomachine engine having the blade are disclosed. The blade includes an airfoil having a root portion, a tip portion, and a plurality of fins integrally coupled to the root portion. The plurality of fins is disposed along a thickness of the airfoil.
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