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公开(公告)号：US20240295259A1
公开(公告)日：2024-09-05
申请号：US18661105
申请日：2024-05-10
Applicant: General Electric Company , GE Avio S.r.I.
Inventor： Andrea Piazza , Ravindra Shankar Ganiger
CPC classification number: F16H55/088 , F16H57/02 , F16H2057/02039
Abstract: A gearbox assembly includes a first gear and a second gear. The first gear includes a plurality of first gear teeth. The second gear includes a plurality of second gear teeth. The plurality of first gear teeth and the plurality of second gear teeth mesh with each other as the first gear and the second gear rotate. A profile shape of at least one first gear tooth of the first gear is characterized by a total profile modification between 66 micrometers and 120 micrometers.
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公开(公告)号：US20240133347A1
公开(公告)日：2024-04-25
申请号：US18400762
申请日：2023-12-29
Applicant: General Electric Company , GE Avio S.r.I.
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：US20240318573A1
公开(公告)日：2024-09-26
申请号：US18357282
申请日：2023-07-24
Inventor： Sajinu Nangariyil , Ravindra Shankar Ganiger , Abhilash Pillai , Adam Tomasz Pazinski , David Raju Yamarthi
IPC: F01D11/08
CPC classification number: F01D11/08 , F05D2220/323 , F05D2240/55
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 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 including a magnet assembly having a magnet coupled to the carrier or the seal segment for biasing the first seal segment along the radial direction.
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公开(公告)号：US12234748B2
公开(公告)日：2025-02-25
申请号：US18334799
申请日：2023-06-14
Inventor： Eyitayo James Owoeye , Ravindra Shankar Ganiger , Adam Tomasz Pazinski
Abstract: A gas turbine engine is provided having a plurality of outlet guide vanes, each defining an internal thermal fluid passageway. The engine defining an Outlet Guide Vane Cooling Capacity greater than 0.01 and less than 13, wherein OGVCC equals: [ HTSA OGV × BPR ( BPR + 1 ) × C a i r × ( T i n l e t - T a i r ) × v f l i g h t × D f a n F n T o t a l × v tip speed × Δ H ] 1 / 3 , and wherein HTSA OGV = N v a n e × D fan 2 × ( 1 - R OGV _ ratio 2 ) 2 × sin ( 180 / N v a n e ) × sin θ OGV × f OGV .
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公开(公告)号：US20240418094A1
公开(公告)日：2024-12-19
申请号：US18334799
申请日：2023-06-14
Inventor： Eyitayo James Owoeye , Ravindra Shankar Ganiger , Adam Tomasz Pazinski
Abstract: A gas turbine engine is provided having a plurality of outlet guide vanes, each defining an internal thermal fluid passageway. The engine defining an Outlet Guide Vane Cooling Capacity greater than 0.01 and less than 13, wherein OGVCC equals: [ HTSA OGV × BPR ( BPR + 1 ) × C air × ( T inlet - T air ) × v flight × D fan Fn Total × v tip speed × Δ H ] 1 / 3 , and wherein HTSA OGV = N vane × D fan 2 × ( 1 - R OGV _ ratio 2 ) 2 × sin ( 180 / N vane ) × sin θ OGV × f OGV .
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Patent Agency Ranking
公开(公告)号：US20240418096A1
公开(公告)日：2024-12-19
申请号：US18357410
申请日：2023-07-24
Inventor： Rajesh Kumar , Sesha Subramanian , Vaishnav Raghuvaran , Ravindra Shankar Ganiger , Adam Tomasz Pazinski
Abstract: A gas turbine engine includes a compressor section comprising a compressor, a combustion section, and a turbine section arranged in serial flow order and defining a working gas flowpath, the compressor comprising an aft-most compressor stage; a spool drivingly coupled to the compressor; a stage of stator vanes located downstream of the aft-most compressor stage; and a stator case, the spool and the stator case together defining a rotor cavity in fluid communication with the working gas flowpath, the stage of stator vanes including a first stator vane defining a fluid passage, and the stator case defining a plenum and a supplemental airflow passage, the plenum in fluid communication with the fluid passage in the first stator vane, the supplemental airflow passage in fluid communication with the plenum and the rotor cavity for proving an airflow to the rotor cavity
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公开(公告)号：US20250163829A1
公开(公告)日：2025-05-22
申请号：US18435651
申请日：2024-02-07
Applicant: General Electric Company
Inventor： Brandon W. Miller , Andrew Hudecki , Ryan T. Roehm , Ravindra Shankar Ganiger
Abstract: A lubrication system for a turbine engine having one or more rotating components. The lubrication system includes a primary reservoir that stores a lubricant therein. A primary lubrication system supplies the lubricant from the primary reservoir to the one or more rotating components during normal operation of the turbine engine. An auxiliary lubrication system includes an auxiliary reservoir in fluid communication with the primary reservoir and the one or more rotating components. The auxiliary reservoir receives the lubricant from the primary reservoir and is positioned at substantially a six o'clock position of the turbine engine. The auxiliary lubrication system supplies the lubricant from the auxiliary reservoir to the one or more rotating components based on at least one of a pressure of the lubricant in the primary lubrication system, a pressure of fuel in the turbine engine, or a pressure of hydraulics of the turbine engine.
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公开(公告)号：US20250154879A1
公开(公告)日：2025-05-15
申请号：US18917860
申请日：2024-10-16
Applicant: General Electric Company
Inventor： Santosh Kumar Potnuru , Pradeep Sangli , Ravindra Shankar Ganiger , Souvik Math , Duane Anstead , Matthew D. Brothers
Abstract: Bearing assemblies for a turbomachine include a first race statically coupled to a fixed engine housing, a second race coupled to a rotating shaft, a bearing cage disposed between the first race and the second race, and at least one bearing element disposed in the bearing cage. The bearing cage can include inlet channels to allow air to flow into the bearing cage and outlet channels that allow the air and lubricant mixture in the bearing cage to vent into adjacent compartments of the turbomachine. During operation, the inlet channels actively direct an airflow into the bearing cage. In the bearing cage, the air mixes with lubricant, and the air and lubricant mixture is expelled from the bearing cage through the outlet channels, thereby reducing dwell time of lubricant in the bearing assembly.
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公开(公告)号：US20250137406A1
公开(公告)日：2025-05-01
申请号：US19006941
申请日：2024-12-31
Applicant: General Electric Company
Inventor： Pradeep Hemant Sangli , Santosh Kumar Potnuru , Keith A. Miedema , Matthew D. Brothers , Ravindra Shankar Ganiger
Abstract: Separators for use with gas turbine engines are disclosed herein. An example cabin bleed system disclosed herein includes a bleed line coupled to a gas turbine engine, a separator defining a cavity fluidly coupled to the bleed line, the separator including a first ring including a first opening fluidly coupled to the cavity. a second ring surrounding the first ring, the second ring including a second opening fluidly coupled to a cabin of an aircraft, and a filter disposed in a fluid pathway extending between the first opening and the second opening.
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公开(公告)号：US12286889B2
公开(公告)日：2025-04-29
申请号：US18350496
申请日：2023-07-11
Applicant: General Electric Company
Inventor： Avinash Natarajan , Vishnu Vardhan Venkata Tatiparthi , Ravindra Shankar Ganiger , Nagashiresha G , Prateek Mathur , Michał Tomasz Kuropatwa , Arthur W Sibbach
Abstract: Systems, apparatus, articles of manufacture, and methods are disclosed to improve fan operability control using smart materials. An engine comprising an engine surface in an airflow path, a sensor positioned on the engine surface, and a smart-material-based feature positioned on the engine surface, the smart-material-based feature triggered to modify the airflow path when the sensor outputs an indication of a detected deviation from a reference value of an operating parameter of the engine.
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