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公开(公告)号：US20230366545A1
公开(公告)日：2023-11-16
申请号：US17931646
申请日：2022-09-13
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Hiranya Nath
CPC classification number: F23R3/002 , F23R3/60 , F02C7/00 , F23R2900/03043 , F05D2220/32 , F05D2240/35
Abstract: A combustor includes a skeleton mesh structure having a plurality of structural elements configured to mesh together to form the skeleton mesh structure. The combustor also includes an inner liner and an outer liner mounted to the skeleton mesh structure to define a combustion chamber. The inner liner includes a plurality of inner planks mounted to an inner side of the inner liner and a plurality of outer planks mounted to an outer side of the inner liner. The outer liner includes a plurality of inner planks mounted to an inner side of the outer liner and a plurality of outer planks mounted to the outer side of the outer liner.
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公开(公告)号：US20230358181A1
公开(公告)日：2023-11-09
申请号：US18353741
申请日：2023-07-17
Applicant: General Electric Company
Inventor： Thomas Malkus , Trevor H. Wood , Giridhar Jothiprasad , Nageswar Ganji , Hiranya Kumar Nath , Ravindra Shankar Ganiger , Ambika Shivamurthy
CPC classification number: F02C9/18 , F01D17/105 , F04D27/0215 , F04D27/023 , F02C7/052 , F05D2250/42
Abstract: Aero-acoustically damped bleed valves are disclosed. An example variable bleed valve apparatus comprises a variable bleed valve door to actuate the variable bleed valve apparatus, and a variable bleed valve port including an upstream edge and a downstream edge, the VBV port to define a secondary flowpath, the VBV door to cover the VBV port in a closed position, and a vortex device at the upstream edge of the variable bleed valve port, the vortex device including a vorticity generating feature along the upstream edge of the variable bleed valve port.
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公开(公告)号：US20230340911A1
公开(公告)日：2023-10-26
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 , F16H57/08 , F16H57/025
CPC classification number: F02C7/36 , F16H57/08 , F16H57/025
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：US11761631B2
公开(公告)日：2023-09-19
申请号：US17806576
申请日：2022-06-13
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Hiranya Nath , Sripathi Mohan
CPC classification number: F23R3/002 , F23R3/007 , F23R3/50 , F23R2900/00017 , F23R2900/03043
Abstract: A dome structure for a combustor of a gas turbine includes a frame structure extending circumferentially about a combustor centerline axis, and a plurality of integrated dome-deflector plate members mounted to the frame structure. Each of the plurality of integrated dome-deflector plate members includes a dome wall, a deflector wall, and a plurality of side walls connecting the dome wall and the deflector wall to each other. A cavity is defined by the dome wall, the deflector wall, and the plurality of side walls.
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公开(公告)号：US11753942B1
公开(公告)日：2023-09-12
申请号：US17717272
申请日：2022-04-11
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Hiranya Kumar Nath , Kirti Arvind Petkar , Viswanadha Gupta Sakala , Nicholas Joseph Kray
CPC classification number: F01D5/147 , F01D5/10 , F01D5/16 , F01D5/28 , F01D21/045 , F04D29/324
Abstract: An airfoil for gas turbine engines is generally provided. The airfoil defines a span extending between a root and a tip, the airfoil further defines a chord at each point along the span extending between a leading edge and a trailing edge. Further, the airfoil includes at least one frangible airfoil portion, a residual airfoil portion adjacent to the at least one frangible airfoil portion, and one or more zones. The one or more zones may include a plurality of cavities, where at least one or more cavities of the plurality of cavities include inclusions, with the inclusions having one or more materials.
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Patent Agency Ranking
公开(公告)号：US11747019B1
公开(公告)日：2023-09-05
申请号：US17929359
申请日：2022-09-02
Applicant: General Electric Company
Inventor： Hiranya Nath , Ravindra Shankar Ganiger , Michael A. Benjamin , Steven C. Vise , Perumallu Vukanti , Sripathi Mohan , Rimple Rangrej
CPC classification number: F23R3/06 , F23R3/16 , F23R3/46 , F23R3/50 , F23R2900/03043
Abstract: A combustor liner has an annular outer liner and an annular inner liner that define a combustion chamber therebetween, the combustion chamber having a dilution zone. The annular outer liner and the annular inner liner each has a converging-diverging section extending into the dilution zone of the combustion chamber that form a throat between them. Each of the converging-diverging sections includes at least one dilution opening defined through the respective converging-diverging section at the throat for providing a flow of an oxidizer through a respective liner to the dilution zone of the combustion chamber.
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公开(公告)号：US11739698B2
公开(公告)日：2023-08-29
申请号：US17684172
申请日：2022-03-01
Applicant: General Electric Company
Inventor： Thomas Malkus , Trevor H. Wood , Giridhar Jothiprasad , Nageswar Ganji , Hiranya Kumar Nath , Ravindra Shankar Ganiger , Ambika Shivamurthy
CPC classification number: F02C9/18 , F01D17/105 , F02C7/052 , F04D27/023 , F04D27/0215 , F05D2250/42
Abstract: Aero-acoustically damped bleed valves are disclosed. An example variable bleed valve apparatus comprises a variable bleed valve door to actuate the variable bleed valve apparatus, and a variable bleed valve port including an upstream edge and a downstream edge, the VBV port to define a secondary flowpath, the VBV door to cover the VBV port in a closed position, and a vortex device at the upstream edge of the variable bleed valve port, the vortex device including a vorticity generating feature along the upstream edge of the variable bleed valve port.
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公开(公告)号：US20230228220A1
公开(公告)日：2023-07-20
申请号：US17684172
申请日：2022-03-01
Applicant: General Electric Company
Inventor： Thomas Malkus , Trevor H. Wood , Giridhar Jothiprasad , Nageswar Ganji , Hiranya Kumar Nath , Ravindra Shankar Ganiger , Ambika Shivamurthy
CPC classification number: F02C9/18 , F01D17/105 , F02C7/052 , F04D27/0215 , F04D27/023 , F05D2250/42
Abstract: Aero-acoustically damped bleed valves are disclosed. An example variable bleed valve apparatus comprises a variable bleed valve door to actuate the variable bleed valve apparatus, and a variable bleed valve port including an upstream edge and a downstream edge, the VBV port to define a secondary flowpath, the VBV door to cover the VBV port in a closed position, and a vortex device at the upstream edge of the variable bleed valve port, the vortex device including a vorticity generating feature along the upstream edge of the variable bleed valve port.
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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：US20230184135A1
公开(公告)日：2023-06-15
申请号：US17655451
申请日：2022-03-18
Applicant: General Electric Company
Inventor： Bugra H. Ertas , Norman A. Turnquist , Ravindra Shankar Ganiger , Gontla Nagashiresha
CPC classification number: F01D25/243 , F01D25/28 , F02C7/36 , F05D2240/14 , F05D2250/75 , F05D2250/13 , F05D2260/31 , F05D2260/38 , F05D2260/40311
Abstract: A windage cover for a plurality of fasteners coupling a ring gear assembly to an output shaft. The windage cover includes a clip retention member abutting an integral cover shell of the output shaft, and a foot portion configured to be inserted into a pilot groove between an integral lip and an arm portion of the output shaft. The windage cover also includes a wall portion connected to the foot portion, the wall portion being retained at one end of the wall portion by the clip retention member. The windage cover is configured to cover the plurality of fasteners.
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