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公开(公告)号：US20240011408A1
公开(公告)日：2024-01-11
申请号：US17894881
申请日：2022-08-24
Applicant: General Electric Company
Inventor： Raghuveer Chinta , Abhijit Roy , Vaishnav Raghuvaran , Srinivas Nuthi , Ravindra Shankar Ganiger
IPC: F01D11/22
CPC classification number: F01D11/22 , F05D2220/32 , F05D2240/55
Abstract: Disclosed herein are example variable flowpath casings for blade tip clearance control. An example casing for a turbine engine includes a first annular substrate extending along an axial direction; a second annular substrate positioned radially inward relative to the first annular substrate, the second annular substrate movably coupled to the first annular substrate; and an actuator coupled to the second annular substrate such that a force applied by the actuator moves the second annular substrate relative to the first annular substrate to adjust a tip clearance.
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公开(公告)号：US11867398B2
公开(公告)日：2024-01-09
申请号：US17931649
申请日：2022-09-13
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Hiranya Nath , Daniel J. Kirtley
CPC classification number: F23R3/002 , F23M5/04 , F23M5/085 , F23R3/06 , F23R3/60 , F23R2900/03041 , F23R2900/03043 , F23R2900/03044
Abstract: A combustor includes an inner liner and an outer liner defining a combustion chamber. The inner liner includes an inner mesh structure, and a plurality of inner planks mounted to the inner mesh structure. The outer liner includes an outer mesh structure, and a plurality of outer planks mounted to the outer mesh structure. Each of the plurality of inner planks and outer planks includes an inner wall, an outer wall, and lateral walls defining a cavity to allow circulation of airflow within the cavity to cool down the inner wall.
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公开(公告)号：US11859823B2
公开(公告)日：2024-01-02
申请号：US17931653
申请日：2022-09-13
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Hiranya Nath , Daniel J. Kirtley
CPC classification number: F23R3/60 , F23R3/002 , F23R2900/00012 , F23R2900/00017
Abstract: A combustor includes an inner liner and an outer liner defining a combustion chamber. The inner liner includes an inner mesh structure, a plurality of hot side planks mounted to a hot side of the inner mesh structure, and a plurality of cold side planks mounted to a cold side of the inner mesh structure. The outer liner includes an outer mesh structure, a plurality of hot side planks mounted to a hot side of the outer mesh structure, and a plurality of cold side planks mounted to a cold side of the outer mesh structure. The combustor further includes a plurality of clips configured to couple the plurality of hot side planks and the plurality of cold side planks to a plurality of structural elements of the inner mesh structure and the outer mesh structure.
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公开(公告)号：US20230417415A1
公开(公告)日：2023-12-28
申请号：US18464550
申请日：2023-09-11
Applicant: General Electric Company
Inventor： Pradeep Naik , Rimple Rakeshkumar Rangrej , Saket Singh , Narasimha Chiranthan R. , Shai Birmaher , Hiranya Kumar Nath , Ravindra Shankar Ganiger
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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公开(公告)号：US20230407793A1
公开(公告)日：2023-12-21
申请号：US18068031
申请日：2022-12-19
Applicant: General Electric Company
Inventor： Mohan Kannaiah Raju , Subramani Adhiachari , Ravindra Shankar Ganiger , Arvind Namadevan , Prasant Bilaiya , Scott Alan Schimmels
CPC classification number: F02C7/24 , F02C7/222 , F02C7/06 , F05D2240/15 , F05D2260/231 , F05D2300/603
Abstract: An insulation assembly for use in a gas turbine engine is provided. The insulation assembly defines a hot side and an insulated side and includes: a heat shield layer positioned proximate the hot side; and a thermal absorption layer positioned proximate the insulated side, the thermal absorption layer comprising a phase change material, the insulation assembly defining an air gap positioned between the heat shield layer and the thermal absorption layer.
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Patent Agency Ranking
公开(公告)号：US20230399983A1
公开(公告)日：2023-12-14
申请号：US17806574
申请日：2022-06-13
Applicant: General Electric Company , GE Avio S.r.l.
Inventor： Ravindra Shankar Ganiger , Andrea Piazza , Gontla Nagashiresha , Bugra H. Ertas , Sanjeev Jha
CPC classification number: F02C7/36 , F01D15/10 , F02K3/06 , F05D2220/768 , F05D2260/40311
Abstract: A differential gearbox assembly for a turbine engine having a fan shaft and a drive shaft. The differential gearbox assembly includes an epicyclic gear assembly coupling the fan shaft to the drive shaft. The epicyclic gear assembly includes a sun gear, a planet gear constrained by a planet carrier, and a ring gear. The sun gear is coupled to the drive shaft and the planet carrier is coupled to the fan shaft. The sun gear, the planet gear, and the ring gear all rotate about the drive shaft. The differential gearbox assembly includes an electric machine assembly that includes an input coupled to the epicyclic gear assembly. The electric machine assembly provides mechanical power to the fan shaft through the epicyclic gear assembly.
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公开(公告)号：US20230383666A1
公开(公告)日：2023-11-30
申请号：US18196949
申请日：2023-05-12
Applicant: General Electric Company
Inventor： Srinivasan Swaminathan , Anand Madihalli Srinivasan , Shalini Thimmegowda , Ravindra Shankar Ganiger
CPC classification number: F01D11/001 , F01D25/183 , F05D2300/224 , F05D2260/98 , F05D2240/55
Abstract: This disclosure is directed to seal assemblies for a turbomachine. The seal assemblies include stationary and rotating components and at least one interface between the stationary and rotating components. The seal assembly further includes a self-lubricating lattice element made of carbon or a carbon-based material. The self-lubricating lattice element may have a porous and compressible microstructure capable of retaining a liquid substance. During engine operation, the self-lubricating lattice element can compress and expel some portion of the liquid substance to form a liquid-containing layer between the rotating and stationary components of the seal assembly. Also described herein are self-lubricating wear sleeves for use in other portions of the turbomachine.
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公开(公告)号：US20230358255A1
公开(公告)日：2023-11-09
申请号：US17840414
申请日：2022-06-14
Applicant: General Electric Company
Inventor： David Raju Yamarthi , Ravindra Shankar Ganiger , Mohan Kannaiah Raju , Prachi Anand Tappu , Santosh Pattnaik , Shishir Paresh Shah , Adam Joseph Wangler
IPC: F04D29/70 , F04D13/06 , F04D29/049 , F04D29/06
CPC classification number: F04D29/708 , F04D13/06 , F04D29/049 , F04D29/061
Abstract: Oil lubricated supercritical fluid pumps with oil separators are disclosed herein. An example pump system to pressurize a fluid within a closed loop thermal transport bus disclosed herein includes a pump housing, a duct fluidly coupled to the pump housing, a first portion of the duct to include a mixture of an oil and the supercritical fluid, a second portion of the duct to include the supercritical fluid, and a separator positioned in a third portion of the duct between the first portion of the duct and the second portion of the duct, the separator to separate the oil in the mixture from the supercritical fluid.
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公开(公告)号：US20230358247A1
公开(公告)日：2023-11-09
申请号：US17840406
申请日：2022-06-14
Applicant: General Electric Company
Inventor： David Raju Yamarthi , Ravindra Shankar Ganiger , Adam Joseph Wangler , Mohan Kannaiah Raju , Prachi Anand Tappu , Santosh Kumar Pattnaik , Shishir Paresh Shah , Brandon W. Miller , Daniel A. Niergarth , Kevin Edward Hinderliter
IPC: F04D29/06 , F04D13/06 , F04D29/046 , F04D1/00
CPC classification number: F04D29/046 , F04D1/00 , F04D13/06 , F04D29/061
Abstract: A pump system to pressurize a fluid within a closed loop transport bus is disclosed herein. The example of the pump system disclosed herein includes a pump, including an impeller, to increase kinetic energy of a fluid flowing through the impeller; an electric motor, including a rotor shaft connected to the impeller, to provide torque to the rotor shaft; a first bearing to support the rotor shaft at a first operational speed range, the first bearing coupled to an inner race; a second bearing to support the rotor shaft at a second operational speed range, the rotor shaft coupled to an outer race; and one or more sprag elements configured to: engage the inner race with the outer race at the first operational speed range; and disengage the inner race from the outer race at the second operational speed range.
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公开(公告)号：US20230341125A1
公开(公告)日：2023-10-26
申请号：US17820373
申请日：2022-08-17
Applicant: General Electric Company
Inventor： Hiranya Nath , Karthikeyan Sampath , Perumallu Vukanti , Ravindra Shankar Ganiger , Pradeep Naik
IPC: F23R3/06
CPC classification number: F23R3/06
Abstract: A combustor liner for a gas turbine includes a liner at least partially defining a combustion chamber. The liner includes a plurality of dilution openings therethrough, at least one dilution opening of the plurality of dilution openings defined by (a) a main dilution opening portion defining a main dilution opening perimeter, and (b) a plurality of secondary dilution opening portions arranged about the main dilution opening perimeter and extending outward from the main dilution opening portion.
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