公开(公告)号：US20230288065A1

公开(公告)日：2023-09-14

申请号：US17810678

申请日：2022-07-05

Applicant: General Electric Company

Inventor： Saket Singh ,  Ravindra Shankar Ganiger ,  Hiranya Nath ,  Perumallu Vukanti ,  Ajoy Patra ,  Karthikeyan Sampath ,  Pradeep Naik ,  Rimple Rangrej ,  Veera Venkata Amarnath Manem

IPC: F23R3/00 ,  F23R3/60

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

Abstract: A dome-deflector assembly for a gas turbine includes a dome, a deflector, and at least one dome-deflector connecting assembly that includes a connecting member connecting the dome and the deflector together with a cavity being defined between the dome and the deflector. The connecting member extends through the deflector and has a first end arranged at a hot surface side of the deflector and a second end arranged to connect with the dome. The dome-deflector connecting assembly is configured to provide a flow of cooling air from the cavity to the hot surface side of the deflector to cool the first end of the connecting member on the hot surface side of the deflector.

公开(公告)号：US20230235884A1

公开(公告)日：2023-07-27

申请号：US17685883

申请日：2022-03-03

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Pradeep Naik ,  Manampathy G. Giridharan ,  Michael T. Bucaro ,  Ajoy Patra ,  Perumallu Vukanti ,  R Narasimha Chiranthan ,  Gregory A. Boardman

IPC: F23R3/00 ,  F02C3/04

CPC classification number: F23R3/002 ,  F02C3/04 ,  F05D2240/35

Abstract: A turbine engine can include a compressor section, a combustion section, and a turbine section in serial flow arrangement. The combustion section can have a combustor with a combustor liner at least partially defining a combustion chamber, as well as a fuel-air mixer including at least one set of mixing tubes.

公开(公告)号：US20230213194A1

公开(公告)日：2023-07-06

申请号：US17699735

申请日：2022-03-21

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Pradeep Naik ,  Manampathy G. Giridharan ,  Ajoy Patra ,  R Narasimha Chiranthan

IPC: F23R3/28 ,  F23R3/14

CPC classification number: F23R3/286 ,  F23R3/14 ,  F23R2900/03042

Abstract: A turbine engine can include a compressor section, a combustion section, and a turbine section in serial flow arrangement. The combustion section can include a combustor with a fuel premixer. The fuel premixer can include an annular shroud defining an interior, a center body located within the interior, and an annular swirler located within the interior.

公开(公告)号：US20230212984A1

公开(公告)日：2023-07-06

申请号：US17692411

申请日：2022-03-11

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Steven C. Vise ,  Pradeep Naik ,  Perumallu Vukanti ,  Michael T. Bucaro ,  Ajoy Patra ,  R Narasimha Chiranthan ,  Michael A. Benjamin ,  Manampathy G. Giridharan ,  Hiranya Kumar Nath

IPC: F02C7/232 ,  F23R3/28

CPC classification number: F02C7/232 ,  F23R3/28 ,  F05D2220/32 ,  F05D2240/35

Abstract: An engine can utilize a combustor to combust fuel to drive the engine. A fuel nozzle assembly can supply fuel to the combustor for combustion or ignition of the fuel. The fuel nozzle assembly can include a swirler and a fuel nozzle to supply a mixture of fuel and air for combustion. Varying the geometry of the swirler can provide for improved supply of air, which can improve efficiency and flame control.

公开(公告)号：US20230194094A1

公开(公告)日：2023-06-22

申请号：US17677165

申请日：2022-02-22

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Fei Han ,  Ramal Janith Samarasinghe ,  Pradeep Naik ,  Krishnakumar Venkatesan ,  Michael T. Bucaro ,  Ajoy Patra ,  Manampathy G. Giridharan

IPC: F23R3/16 ,  F02C3/00 ,  F02C7/22 ,  F23R3/36

CPC classification number: F23R3/16 ,  F02C3/00 ,  F02C7/22 ,  F23R3/36

Abstract: A turbine engine having a compressor section, a combustion section and a turbine section in serial flow arrangement. The turbine engine further having a combustor, provided within the combustion section, defining a combustion chamber and having at least one fuel injector. The fuel injector having a fuel channel, a first set of fuel orifices, and a flow restrictor located within the fuel channel and having a second set of fuel orifices.

公开(公告)号：US20230194088A1

公开(公告)日：2023-06-22

申请号：US17686800

申请日：2022-03-04

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Manampathy G. Giridharan ,  Clayton S. Cooper ,  Michael A. Benjamin ,  Steven C. Vise ,  Michael T. Bucaro ,  Ajoy Patra ,  Pradeep Naik ,  Perumallu Vukanti ,  R Narasimha Chiranthan

IPC: F23R3/06 ,  F23R3/28

CPC classification number: F23R3/06 ,  F23R3/286 ,  F23R2900/03044

Abstract: A turbine engine and method for controlling nitrogen oxides present within a combustor of the turbine engine. The turbine engine having a compressor section, a combustion section, and a turbine section in serial flow arrangement along an engine centerline. The combustion section having a combustor liner having a first end, a second end, opposing the first end, and at least partially defining a combustion chamber extending between the first and second ends. A dome assembly is mounted to the combustor liner at the first end and defines a dome inlet of the combustion chamber. There are multiple sets of dilution holes including a first set of dilution holes provided in the combustor liner downstream from the dome inlet and a second set of dilution holes provided in the combustor liner between the first set of dilution holes and the dome inlet.

公开(公告)号：US11649966B1

公开(公告)日：2023-05-16

申请号：US17689070

申请日：2022-03-08

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Ajoy Patra ,  Pradeep Naik ,  Perumallu Vukanti ,  Michael T. Bucaro ,  R Narasimha Chiranthan ,  Manampathy G. Giridharan ,  Michael A. Benjamin ,  Clayton S. Cooper

IPC: F23R3/28 ,  F02C7/264 ,  F23R3/04 ,  F23R3/50 ,  F23D14/64

CPC classification number: F23R3/286 ,  F02C7/264 ,  F23D14/64 ,  F23R3/045 ,  F23R3/50 ,  F05D2240/35 ,  F05D2260/99 ,  F23D2207/00

Abstract: A turbine engine having a combustion section. The combustion section can have a combustor, at least one fuel cup, and at least one ignition tube. The combustor can include a combustor liner and a dome wall, which together at least partially define a combustion chamber. The at least one fuel cup can include a swirler and a fuel injector. The at least one ignition tube can include an outlet directly fluidly coupled to the combustion chamber.

公开(公告)号：US20250020325A1

公开(公告)日：2025-01-16

申请号：US18901941

申请日：2024-09-30

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Manampathy G. Giridharan ,  Ajoy Patra ,  Pradeep Naik ,  R Narasimha Chiranthan ,  Perumallu Vukanti ,  Michael T. Bucaro

IPC: F23R3/28

Abstract: A turbine engine that includes an engine core having at least a compressor section and a combustion section. The combustion section includes a combustor. The combustor section or combustor includes a fuel-air mixing assembly fluidly coupled to the compressor section. The fuel-air mixing assembly includes an outer wall, a center body at least partially circumscribed by the outer wall, and an annular flow passage between the outer wall and center body. At least one fuel orifice includes a fuel outlet fluidly coupled to the annular flow passage.

公开(公告)号：US20250020324A1

公开(公告)日：2025-01-16

申请号：US18435282

申请日：2024-02-07

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Manampathy G. Giridharan ,  Clayton S. Cooper ,  Michael A. Benjamin ,  Steven C. Vise ,  Michael T. Bucaro ,  Ajoy Patra ,  Pradeep Naik ,  Perumallu Vukanti ,  R Narasimha Chiranthan

IPC: F23R3/06 ,  F23R3/28

Abstract: A turbine engine and method for controlling nitrogen oxides present within a combustor of the turbine engine. The turbine engine having a compressor section, a combustion section, and a turbine section in serial flow arrangement along an engine centerline. The combustion section having a combustor liner having a first end, a second end, opposing the first end, and at least partially defining a combustion chamber extending between the first and second ends. A dome assembly is mounted to the combustor liner at the first end and defines a dome inlet of the combustion chamber. There are multiple sets of dilution holes including a first set of dilution holes provided in the combustor liner downstream from the dome inlet and a second set of dilution holes provided in the combustor liner between the first set of dilution holes and the dome inlet.

公开(公告)号：US12152780B2

公开(公告)日：2024-11-26

申请号：US18302346

申请日：2023-04-18

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Ajoy Patra ,  Pradeep Naik ,  Perumallu Vukanti ,  Michael T. Bucaro ,  R Narasimha Chiranthan ,  Manampathy G. Giridharan ,  Michael A. Benjamin ,  Clayton S. Cooper

IPC: F23R3/28 ,  F02C7/264 ,  F23D14/64 ,  F23R3/04 ,  F23R3/50

Abstract: A method of supplying a first fuel and air mixture and a second fuel and air mixture to a combustor. The combustor having a combustion chamber, a dome wall at least partially defining the combustion chamber, at least one fuel cup provided in the dome wall, and at least one ignition tube having an outlet exhausting to the combustion chamber. The method comprising supplying a first flow of compressed air to only the at least one ignition tube, igniting the first fuel and air mixture, supplying the first ignited fuel and air mixture of the combustion chamber, and supplying a second flow of fuel and a second flow of compressed air to the at least one fuel cup.