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公开(公告)号：US20240026799A1
公开(公告)日：2024-01-25
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
CPC classification number: F01D11/02 , F01D11/12 , F05D2220/30 , F05D2240/55 , F05D2260/80
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：US20230366549A1
公开(公告)日：2023-11-16
申请号：US17931700
申请日：2022-09-13
Applicant: General Electric Company
Inventor： Hiranya Nath , Ravindra Shankar Ganiger , Sripathi Mohan
CPC classification number: F23R3/06 , F02C7/04 , F23R2900/03044
Abstract: A combustor includes a skeleton mesh structure having a plurality of structural elements configured to mesh together to form the skeleton mesh structure, each of the plurality of structural elements including a frame and, a plurality of louvers connected to the frame. The combustor also includes an inner liner mounted to the skeleton mesh structure to define a combustion chamber. The inner liner includes a plurality of inner planks mounted to the skeleton mesh structure, each of the plurality of inner planks being mounted to a corresponding one of the plurality of structural elements.
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公开(公告)号：US20230324047A1
公开(公告)日：2023-10-12
申请号：US17812897
申请日：2022-07-15
Applicant: General Electric Company
Inventor： Vijayaraj Sukumar , Perumallu Vukanti , Pradeep Naik , Ajoy Patra , Karthikeyan Sampath , Rimple Rangrej , Hiranya Nath , Krishnendu Chakraborty , Narasimhan S. Sahana , Saket Singh , Ravindra Shankar Ganiger
CPC classification number: F23R3/002 , F23R2900/03045 , F23R2900/00017 , F23R3/60
Abstract: A deflector assembly for a combustor defining an operational fluid flow. The deflector assembly includes an upstream surface and a downstream surface opposite the upstream surface. One or more fastening mechanisms each extends through the deflector assembly. One or more cooling holes extend through the deflector assembly from the upstream surface to the downstream surface. The one or more cooling holes are located about the one or more fastening mechanisms to operably direct cooling air about the one or more fastening mechanisms at the downstream surface.
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公开(公告)号：US20230313688A1
公开(公告)日：2023-10-05
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 , F05D2240/24 , F05D2230/80 , F05D2220/32
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：US11774098B2
公开(公告)日：2023-10-03
申请号：US17340585
申请日：2021-06-07
Applicant: General Electric Company
Inventor： Pradeep Naik , Rimple Rakeshkumar Rangrej , Saket Singh , Narasimha Chiranthan R , Shai Birmaher , Hiranya Kumar Nath , Ravindra Shankar Ganiger
CPC classification number: F23R3/16 , F23R3/002 , F23R3/06 , F23R3/08 , F23R3/346 , F23M5/085 , F23M2900/05002 , F23R2900/00014 , F23R2900/03042
Abstract: A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor including: a forward liner segment; an aft liner segment disposed downstream from the forward liner segment relative to a direction of flow through the combustor, the forward and aft liner segments at least partially defining a combustion chamber; and a fence disposed between the forward and aft liner segments, wherein the fence extends in the circumferential direction, and wherein the fence extends into the combustion chamber along the radial direction.
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Patent Agency Ranking
公开(公告)号：US20230272912A1
公开(公告)日：2023-08-31
申请号：US17809629
申请日：2022-06-29
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Hiranya Nath , Sripathi Mohan , Girish Kamath Cannanore
CPC classification number: F23R3/60 , F23R3/002 , F23R2900/00014 , F23R2900/00017 , F23R2900/03044
Abstract: A combustor for a gas turbine includes a dome, and a deflector connected to the dome to define a baffle cavity therebetween, the deflector having a deflector cold side adjacent to the baffle cavity and a deflector hot side adjacent to a combustion chamber. At least one dome-deflector connecting member connects the dome and the deflector to each other. The dome-deflector connecting member forms a flexible joint between the dome and the deflector.
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公开(公告)号：US20230272751A1
公开(公告)日：2023-08-31
申请号：US17813677
申请日：2022-07-20
Applicant: General Electric Company
Inventor： David Yamarthi , Paul Mathew , Parmeet Chhabra , Ravindra Shankar Ganiger , Souvik Porel , Gautam Naik , Norman A. Turnquist
CPC classification number: F02C7/36 , F02C7/06 , F05D2250/291 , F05D2260/232 , F05D2260/40311 , F05D2260/96 , F05D2260/98 , F05D2300/612
Abstract: A gearbox assembly for a gas turbine engine includes a hollow gear. The hollow gear has one or more reservoirs configured to store a lubricant and one or more passages configured to supply the lubricant to one or more gear meshes in the gearbox assembly. The hollow gear provides a dampening system configured to absorb vibrations and loading experienced in the gearbox assembly and configured to provide impact resistance for the gearbox assembly.
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公开(公告)号：US20230266007A1
公开(公告)日：2023-08-24
申请号：US17809381
申请日：2022-06-28
Applicant: General Electric Company
Inventor： Ranganatha Narasimha Chiranthan , Karthikeyan Sampath , Perumallu Vukanti , Rimple Rangrej , Ravindra Shankar Ganiger , Hiranya Nath
CPC classification number: F23R3/16 , F23R3/06 , F23R2900/00001 , F23R2900/03045 , F23R2900/03044
Abstract: A combustor liner for a gas turbine has a cold side liner segment, and a hot side liner segment, with a baffle cavity between the cold side liner segment and the hot side liner segment. At least one cooling airflow dispersing member is arranged within the baffle cavity. The at least one cooling airflow dispersing member includes a main cavity portion, and at least one peripheral cavity portion surrounding the main cavity portion. The main cavity portion includes a main cavity inlet side having a cooling airflow opening, a main cavity outlet side having plurality of hot side cooling airflow openings, and at least one peripheral cavity outlet flow passage providing fluid communication between the main cavity portion and the at least one peripheral cavity portion. The at least one peripheral cavity portion includes a peripheral cavity outlet side having a plurality of hot side cooling airflow openings.
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公开(公告)号：US11725817B2
公开(公告)日：2023-08-15
申请号：US17363088
申请日：2021-06-30
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Hiranya Kumar Nath , Rajendra Mahadeorao Wankhade , Daniel J. Kirtley , Michael Anthony Benjamin
CPC classification number: F23R3/08 , F01D9/023 , F23R3/002 , F23R3/06 , F23R3/60 , F02C7/28 , F05D2220/32 , F05D2240/35 , F05D2240/55 , F23R3/005
Abstract: A gas turbine engine and combustor assembly are provided, the combustor assembly including a first liner and a second liner together defining at least in part a combustion chamber, wherein the first liner and the second liner are separated by a gap along the longitudinal direction, and wherein the first liner is forward of the second liner relative to a flow of fluid through the combustion chamber along the longitudinal direction, and wherein the gap is extended along the circumferential direction.
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公开(公告)号：US20230250961A1
公开(公告)日：2023-08-10
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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