公开(公告)号：US11788724B1

公开(公告)日：2023-10-17

申请号：US17929360

申请日：2022-09-02

Applicant: General Electric Company

Inventor： Hiranya Nath ,  Ravindra Shankar Ganiger ,  Michael A. Benjamin

IPC: F23R3/00 ,  F23R3/04 ,  F02C7/045

CPC classification number: F23R3/002 ,  F02C7/045 ,  F23R3/04 ,  F05D2240/35 ,  F05D2260/96 ,  F23R2900/00014

Abstract: A combustor liner has an outer liner and an inner liner that define a combustion chamber therebetween, the combustion chamber having a dilution zone. The outer liner and the inner liner each have a converging-diverging section extending into the dilution zone of the combustion chamber and form a throat between them. A bridge member extends across the converging-diverging sections to form a damper cavity therebetween. Each of the converging-diverging sections includes at least one dilution opening defined through the respective converging-diverging section at the throat, and includes a damper inlet feed member on a downstream portion of the converging-diverging section, so that an acoustic damper is defined by the converting-diverging section, the bridge, and the damper inlet feed. The acoustic damper dampens acoustic characteristics of the combustor.

公开(公告)号：US11781753B2

公开(公告)日：2023-10-10

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

IPC: F23R3/00 ,  F23R3/60 ,  F23R3/50 ,  F23M5/04

CPC classification number: F23R3/60 ,  F23M5/04 ,  F23R3/002 ,  F23R3/50 ,  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.

公开(公告)号：US20230313992A1

公开(公告)日：2023-10-05

申请号：US17811771

申请日：2022-07-11

Applicant: General Electric Company

Inventor： Ranganatha Narasimha Chiranthan ,  Hiranya Nath ,  Girish Kamath Cannanore ,  Ravindra Shankar Ganiger ,  Pradeep Naik ,  Saket Singh ,  Deepti Bhandari ,  Vijayaraj Sukumar

IPC: F23R3/00 ,  F23R3/60

CPC classification number: F23R3/002 ,  F23R3/60 ,  F23R2900/03043 ,  F23R2900/00014 ,  F23R2900/00017

Abstract: A liner assembly for a combustor. The liner assembly includes a liner defining a combustion chamber of the combustor. The liner includes a looped section at a forward end of the liner. The looped section includes one or more bends such that the looped section forms a compliant joint and vibrations are dampened through the liner downstream of the looped section.

公开(公告)号：US11732750B2

公开(公告)日：2023-08-22

申请号：US17192116

申请日：2021-03-04

Applicant: General Electric Company

Inventor： Ravindra Shankar Ganiger ,  Thomas D. Woodrow ,  Weize Kang ,  Praveen Sharma ,  Ambika Shivamurthy

IPC: F16C19/00 ,  F02C7/06 ,  F01D25/16 ,  F03D80/70 ,  F03D13/20

CPC classification number: F16C19/00 ,  F01D25/16 ,  F02C7/06 ,  F03D13/20 ,  F03D80/70 ,  F05B2240/221 ,  F05B2240/50 ,  F05D2240/50 ,  F05D2260/70 ,  F16C2360/31

Abstract: A bearing system is configured to surround a rotor along a circumferential direction corresponding to the rotor. The rotor is extended along an axial direction co-directional to a centerline axis of the rotor. The bearing system includes a body from which a plurality of first support members is each extended, and wherein the plurality of first support members is spaced apart from one another along the circumferential direction. Each first support member includes a first axial support arm extended along the axial direction and a first radial support arm extended from the first axial support arm along a radial direction. The first radial support arm is configured to position a bearing element in contact with a bearing surface at the rotor.

公开(公告)号：US20230249838A1

公开(公告)日：2023-08-10

申请号：US17665286

申请日：2022-02-04

Applicant: General Electric Company

Inventor： Srinivas Addagatla ,  Ravindra Shankar Ganiger ,  Anil Soni ,  Sharad Tiwari ,  Jonathan E. Coleman

IPC: B64D27/26 ,  F01D25/28

CPC classification number: B64D27/26 ,  F01D25/28 ,  B64D2027/262 ,  B64D2027/268 ,  F05D2220/323 ,  F05D2240/90

Abstract: Dual function links for gas turbine engine mounts are disclosed. An example apparatus for mounting a casing of a gas turbine engine to a pylon, the apparatus includes a first pin and a linkage including a first linkage portion including the first pin, a second linkage portion, the second linkage portion forming a first load path between the gas turbine engine and the pylon, the second linkage portion arranged with respect to the first linkage portion such that a gap prevents the first linkage portion from forming a second load path between the gas turbine engine and the pylon.

公开(公告)号：US20230220799A1

公开(公告)日：2023-07-13

申请号：US17663308

申请日：2022-05-13

Applicant: General Electric Company

Inventor： Kudum Shinde ,  Ravindra Shankar Ganiger

IPC: F02C3/04 ,  F04D29/32 ,  F02C7/18 ,  F02C7/36 ,  F02C7/32

CPC classification number: F02C3/04 ,  F02C7/18 ,  F02C7/32 ,  F02C7/36 ,  F04D29/321 ,  F05D2220/323 ,  F05D2240/35 ,  F05D2240/60

Abstract: A gas turbine engine includes a compressor section with a compressor rotor shaft assembly including a plurality of compressor rotors longitudinally spaced apart from each other via respective ones of a plurality of shaft sections of a rotor shaft, each compressor rotor of the plurality of compressor rotors having a plurality of rotor vanes extending radially outward therefrom and being circumferentially spaced about the compressor rotor. A stator shroud assembly has a stator shroud casing surrounding the compressor rotor shaft assembly, a compressor flow passage being defined between the compressor rotor shaft assembly and the stator shroud casing. A pressurized air source generates a flow of pressurized air to be provided to the compressor section, and a plurality of pressurized airflow nozzles are connected with the pressurized air source and provide the flow of pressurized air into the compressor flow passage to cause the compressor rotor shaft assembly to rotate.

公开(公告)号：US20230194087A1

公开(公告)日：2023-06-22

申请号：US17663311

申请日：2022-05-13

Applicant: General Electric Company

Inventor： Saket Singh ,  Pradeep Naik ,  Rimple Rangrej ,  Shai Birmaher ,  Ranganatha Narasimha Chiranthan ,  Ajoy Patra ,  Ravindra Shankar Ganiger ,  Hiranya Nath

IPC: F23R3/06 ,  F23R3/16

CPC classification number: F23R3/06 ,  F23R3/16

Abstract: A combustor liner for a combustor of a gas turbine includes an outer liner extending circumferentially about a combustor centerline, and an inner liner extending circumferentially about the combustor centerline, where the outer liner and the inner liner define a combustion chamber therebetween. At least one of the outer liner and the inner liner includes a dilution flow assembly comprising, (a) an annular slot dilution opening, and (b) a dilution fence extending between an upstream side of the annular slot dilution opening to a downstream side of the annular slot dilution opening, and extending into the combustion chamber, the dilution fence including a plurality of dilution openings therethrough for providing a flow of an oxidizer through the dilution fence into the combustion chamber.

公开(公告)号：US11674399B2

公开(公告)日：2023-06-13

申请号：US17368961

申请日：2021-07-07

Applicant: General Electric Company

Inventor： Ravindra Shankar Ganiger ,  Praveen Sharma ,  Abhijeet Jayshingrao Yadav ,  Nitesh Jain ,  Nicholas Joseph Kray

IPC: F01D5/28 ,  F01D5/14 ,  F01D5/30

CPC classification number: F01D5/282 ,  F01D5/147 ,  F01D5/30 ,  F05C2251/08 ,  F05D2240/303 ,  F05D2240/304 ,  F05D2240/307 ,  F05D2300/505

Abstract: An airfoil arrangement for a gas turbine engine may include a support device using a shape memory alloy to support and control the airfoil. The support device may be formed as part of a fan blade. The arrangement may be configured to reduce overall weight and dimensions of the gas turbine engine.

公开(公告)号：US20230111191A1

公开(公告)日：2023-04-13

申请号：US17543347

申请日：2021-12-06

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Manish Singhal ,  Vishnu Das K ,  Sagar Pradhan ,  Ravindra Shankar Ganiger

IPC: F01D25/24 ,  F01D25/00 ,  F01D5/28 ,  F02C7/25

Abstract: Fire retardant engine casing apparatus are disclosed. An example engine casing includes an inner shell circumferentially surrounding blades of a fan, a compressor, or a turbine, an outer shell positioned around the inner shell, and a fire retardant material between the inner shell and the outer shell.

公开(公告)号：US11603799B2

公开(公告)日：2023-03-14

申请号：US17130040

申请日：2020-12-22

Applicant: General Electric Company

Inventor： Ravindra Shankar Ganiger ,  Hiranya Kumar Nath ,  Michael Anthony Benjamin ,  Rajendra Mahadeorao Wankhade ,  Gurunath Gandikota

IPC: F23R3/28 ,  F02C7/24 ,  F02C7/22

Abstract: A combustor for a gas turbine engine includes an inner liner and an outer liner positioned outward of the inner liner along the radial direction such that a combustion chamber is defined between the inner and outer liners. Furthermore, the combustor includes a fuel nozzle configured to supply fuel to the combustion chamber. Moreover, the combustor includes a bristle pack having a base plate and a plurality of bristles extending outward from the base plate such that the bristle pack forms at least a portion of at least one of a heat shield coupled to the fuel nozzle, a deflector of the combustor, or a flare of the combustor.