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公开(公告)号：US20250043692A1
公开(公告)日：2025-02-06
申请号：US18362346
申请日：2023-07-31
Applicant: General Electric Company
Inventor： David Yamarthi , Tod R. Steen , Ravindra Shankar Ganiger , Kudum Shinde , Ankita Sinha , Aman Srivastava , Narayanan Payyoor , Venkata Subramanya Sarma Devarakonda , Rajesh Kumar Undipalli , Dinesh Rakwal , Himanshu Gupta , Hrishi Ragesh
Abstract: A gas turbine engine includes a fan section having a plurality of fan blades, the fan section configured to generate an airflow through the gas turbine engine, an airflow passage having a core passage and a bypass passage separate from the core passage, a low-speed shaft coupled to and configured to rotate the plurality of fan blades, and a sensor assembly coupled to the gas turbine engine and configured to detect torsional vibration in the low-speed shaft. The sensor assembly includes a plurality of dynamic pressure sensors in the airflow passage. The plurality of dynamic pressure sensors detect a dynamic pressure of the airflow passage that is indicative of the torsional vibration in the low-speed shaft. A damping system is configured to dampen the torsional vibration in the low-speed shaft based on a correlation of a measured torsional vibration and an experimental torsional vibration.
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公开(公告)号：US20250035052A1
公开(公告)日：2025-01-30
申请号：US18913330
申请日：2024-10-11
Applicant: General Electric Company , GE Avio S.r.l.
Inventor： Bugra H. Ertas , Ravindra Shankar Ganiger , Andrea Piazza , Brandon W. Miller
IPC: F02C7/36
Abstract: A mounting assembly for a gearbox assembly of a gas turbine engine includes at least one mounting member configured to mount a gear of the gearbox assembly to a component of the gas turbine engine, the at least one mounting member characterized by a lateral impedance parameter, a bending impedance parameter, and a torsional impedance parameter. A gas turbine engine includes the mounting assembly. The at least one mounting member may be a flex mount, a fan frame, or a flex coupling. The gas turbine engine also includes a heat exchanger including an inner peripheral wall and an outer peripheral wall extending between an inlet and an outlet. The inner peripheral wall and the outer peripheral wall define a flow channel therebetween. The heat exchanger includes a plurality of fins disposed in the flow channel and dividing the flow channel into a plurality of flow passages.
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公开(公告)号：US12203418B2
公开(公告)日：2025-01-21
申请号：US17929105
申请日：2022-09-01
Applicant: General Electric Company , GE Avio S.r.l.
Inventor： Bugra H. Ertas , Ravindra Shankar Ganiger , Andrea Piazza
IPC: F02C7/36 , F16H57/025 , F16H57/08
Abstract: A mounting assembly for a gearbox assembly of a gas turbine engine includes at least one mounting member configured to mount a gear of the gearbox assembly to a component of the gas turbine engine, the at least one mounting member characterized by a lateral impedance parameter, a bending impedance parameter, and a torsional impedance parameter. A gas turbine engine includes the mounting assembly. The at least one mounting member may be a flex mount, a fan frame, or a flex coupling.
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公开(公告)号：US12203375B2
公开(公告)日：2025-01-21
申请号：US17871063
申请日：2022-07-22
Applicant: General Electric Company
Inventor： Narendra Anand Hardikar , Deepak Trivedi , Ravindra Shankar Ganiger , Scott Alan Schimmels , Kevin Richard Graziano
Abstract: A seal assembly at a rotor-stator interface includes at least one non-contacting seal interface and at least one rub detection feature. The rub detection feature(s) is configured to generate a signal upon the rotor and the stator making contact at the rotor-stator interface and causing wear above a certain threshold at the rotor-stator interface. The seal assembly also includes at least one sensor arranged at the rotor-stator interface. The sensor is configured to sense the signal. The seal assembly further includes a controller communicatively coupled with the sensor(s). The controller is configured to receive the signal and estimate at least one of an amount and a location of the wear at the rotor-stator interface based on the signal.
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公开(公告)号：US12188358B2
公开(公告)日：2025-01-07
申请号：US18325621
申请日：2023-05-30
Applicant: General Electric Company
Inventor： Santosh Potnuru , Pradeep Hemant Sangli , Ravindra Shankar Ganiger , Praveen Sharma , Scott Alan Schimmels
Abstract: A seal assembly for a rotary machine. The seal assembly includes a rotor and a stator. The rotor is rotatable about a rotational axis and has a rotor seal face. The stator has a stator seal face. The stator seal face is positioned opposite the rotor seal face and faces the rotor seal face with a gap therebetween. A portion of one of the rotor and the stator is formed of (i) a shape memory alloy or (ii) a first metal and a second metal with the second metal having a coefficient of thermal expansion different from the first metal. The seal assembly is characterized by a seal clearance compliance ratio (SCCR) from 20% to 90%.
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Patent Agency Ranking
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：US12146441B1
公开(公告)日：2024-11-19
申请号：US18456391
申请日：2023-08-25
Applicant: General Electric Company
Inventor： Paul Mathew , Ravindra Shankar Ganiger , David Raju Yamarthi , Rachamadugu Sivaprasad , Michael Joseph Murray , Hiranya Kumar Nath
Abstract: Methods and apparatus to maintain a state of a fluid in a system are disclosed. An example system includes a pump including a primary inlet, a primary outlet, and a secondary inlet, at least one injector including a first inlet, a second inlet, and at least one outlet, a third conduit coupled to a first conduit upstream of the primary inlet and coupled to the at least one injector at the first inlet to deliver the fluid, a fourth conduit coupled to a second conduit downstream of the primary outlet and coupled to the at least one injector at the second inlet to deliver the fluid, and a fifth conduit coupled to the at least one injector at the at least one outlet to receive the fluid and coupled to the pump at the secondary inlet.
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公开(公告)号：US12116896B1
公开(公告)日：2024-10-15
申请号：US18189408
申请日：2023-03-24
Applicant: General Electric Company
Inventor： Grant Robert Portune , Steven Douglas Johnson , Mallikarjun Metri , Ajith Jogi , Pratish Patil , Nageswar Rao Ganji , Rahul Anil Bidkar , Prateek Jalan , Ravindra Shankar Ganiger , David Raju Yamarthi , Narendra Anand Hardikar , Chandrashekhar Kandukuri
CPC classification number: F01D11/001 , F01D11/025 , F01D11/04 , F01D25/22 , F16J15/40 , F16J15/445 , F16J15/164
Abstract: A turbine engine is provided. The gas turbine engine defines a radial direction and includes: a rotor; a stator comprising a carrier; a seal assembly disposed between the rotor and the stator, the seal assembly comprising a plurality of seal segments, the plurality of seal segments having a seal segment, the seal segment having a seal face configured to form a fluid bearing with the rotor; and a seal support assembly, the seal support assembly comprises a pneumatic engagement assembly operable to bias the seal segment along the radial direction during operation of the turbine engine.
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公开(公告)号：US12110805B2
公开(公告)日：2024-10-08
申请号：US18329467
申请日：2023-06-05
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Viswanadha Gupta Sakala , Nicholas Joseph Kray , Ambika Shivamurthy , Kirti Arvind Petkar
CPC classification number: F01D5/147 , F01D5/02 , G06F30/17 , F05D2220/32 , F05D2230/80 , F05D2240/24
Abstract: Methods, apparatus, systems and articles of manufacture corresponding to a fan blade with intrinsic damping characteristics are disclosed. An example fan blade comprises an exterior body including a first side and a second side; a first hairpin structure in contact with (a) the first side of the exterior body and (b) the second side of the exterior body; and a second hairpin structure in contact with (a) the first side and (b) the second side, wherein the first hairpin structure corresponds to a first stiffness and the second hairpin structure corresponds to a second stiffness different than the first stiffness.
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公开(公告)号：US12104795B2
公开(公告)日：2024-10-01
申请号：US17664975
申请日：2022-05-25
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Hiranya Nath , Michael A. Benjamin
Abstract: A combustor for a gas turbine includes a combustor liner that has an outer liner and an inner liner. At least one of the outer liner and the inner liner includes (a) an upstream liner section fixedly connected in the combustor, (b) a downstream liner section fixedly connected in the combustor, and (c) a dilution liner section including a movable portion including at least a part of the dilution liner section and having at least one dilution opening therethrough. The movable portion is arranged to translate in an upstream direction and in a downstream direction. At least one actuator is connected to the movable portion of the dilution liner section and controls translational movement of the movable portion in the upstream direction and the downstream direction to adjust a volume of a primary combustion zone within the combustor.
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