公开(公告)号：US20250109853A1

公开(公告)日：2025-04-03

申请号：US18476595

申请日：2023-09-28

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Pradeep Naik ,  Perumallu Vukanti ,  Ravindra Shankar Ganiger ,  Sahana Narasimhan Suresh ,  Clayton S. Cooper ,  Michael A. Benjamin ,  Steven C. Vise ,  Sripathi Mohan ,  Hiranya Kumar Nath

IPC: F23R3/00 ,  F23R3/28 ,  F23R3/60

Abstract: A turbine engine with a compressor section, a combustion section, and a turbine section in serial flow arrangement along an engine centerline. The combustion section includes a primary combustor liner including an inner liner and an outer liner. A dome wall and a primary dome inlet are located in the dome wall. The outer liner defines at least one opening downstream from the primary dome inlet. A primary combustion chamber and a set of secondary combustors are fluidly coupled to the primary combustion chamber at the at least one opening.

公开(公告)号：US12031486B2

公开(公告)日：2024-07-09

申请号：US17717636

申请日：2022-04-11

Applicant: GENERAL ELECTRIC COMPANY

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

IPC: F02C7/232 ,  F23R3/34

CPC classification number: F02C7/232 ,  F23R3/34

Abstract: A turbine engine and method of operation with a combustor as shown and described. The turbine engine including a combustor comprising an annular array of rich cups and an annular array of lean cups. A method for controlling nitrogen oxides including injecting a fuel/air mixture from the lean cups and the rich cups.

公开(公告)号：US11994294B2

公开(公告)日：2024-05-28

申请号：US17931700

申请日：2022-09-13

Applicant: General Electric Company

Inventor： Hiranya Nath ,  Ravindra Shankar Ganiger ,  Sripathi Mohan

IPC: F23R3/06 ,  F02C7/04 ,  F23R3/00

CPC classification number: F23R3/06 ,  F02C7/04 ,  F23R3/002 ,  F23R2900/03044

Abstract: A combustor includes a skeleton mesh structure having a plurality of structural elements configured to mesh together to form the skeleton mesh structure, each of the plurality of structural elements including a frame and, a plurality of louvers connected to the frame. The combustor also includes an inner liner mounted to the skeleton mesh structure to define a combustion chamber. The inner liner includes a plurality of inner planks mounted to the skeleton mesh structure, each of the plurality of inner planks being mounted to a corresponding one of the plurality of structural elements.

公开(公告)号：US20230204213A1

公开(公告)日：2023-06-29

申请号：US17691781

申请日：2022-03-10

Applicant: General Electric Company

Inventor： Pradeep Naik ,  Perumallu Vukanti ,  Michael T. Bucaro ,  Ajoy Patra ,  Manampathy G. Giridharan ,  Steven C. Vise ,  Michael A. Benjamin ,  Sripathi Mohan ,  R Narasimha Chiranthan ,  Joseph Zelina

IPC: F23R3/14 ,  F23R3/28

CPC classification number: F23R3/14 ,  F23R3/286 ,  F23D11/383

Abstract: A turbine engine can utilize a combustor to combust fuel to drive the turbine, which drives 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. Increasing efficiency and carbon-containing emission needs benefit from the use of alternative fuels, which combust at higher temperatures than traditional fuels, requiring improved fuel introduction without the occurrence of flame holding or flashback.

公开(公告)号：US20250155124A1

公开(公告)日：2025-05-15

申请号：US18507877

申请日：2023-11-13

Applicant: General Electric Company

Inventor： Joseph Zelina ,  Clayton S. Cooper ,  Sibtosh Pal ,  Pradeep Naik ,  Sripathi Mohan ,  Michael A. Benjamin

IPC: F23R3/34 ,  F02C3/30

Abstract: A turbine engine includes a compressor section for providing a compressed air flow, a fuel system for providing a primary combustor fuel supply, and a secondary combustor fuel supply. A primary combustor, located downstream of the compressor section, combusts the compressed air flow and the primary combustor fuel supply to generate primary combustion products. A turbine section, located downstream of the primary combustor, includes a turbine and a secondary combustor that further combusts the primary combustion products and the fuel from the secondary combustor fuel supply. A steam system provides a steam supply to the secondary combustor. The secondary combustor further combusts the primary combustion products and the secondary combustor fuel supply to generate secondary combustion products, and the turbine section is rotated by the secondary combustor steam supply and the inter-turbine combustion products.

公开(公告)号：US20250067439A1

公开(公告)日：2025-02-27

申请号：US18453506

申请日：2023-08-22

Applicant: General Electric Company

Inventor： Pradeep Naik ,  Clayton S. Cooper ,  Perumallu Vukanti ,  Michael A. Benjamin ,  Steven C. Vise ,  Sripathi Mohan

IPC: F23R3/28

Abstract: A combustor includes a combustion chamber having an outer liner and an inner liner and defining a first combustion zone, an annular dome coupled to the outer liner and the inner liner, and a trapped vortex cavity extending from at least one of the outer liner or the inner liner and defining a second combustion zone. A plurality of first mixing assemblies are disposed through the annular dome, and operably inject a first fuel-air mixture into the first combustion zone. A plurality of second mixing assemblies are disposed at the trapped vortex cavity, and operably inject a second fuel-air mixture into the second combustion zone defined in the trapped vortex cavity to produce combustion gases. A steam system includes a steam injector in fluid communication with the trapped vortex cavity. The steam injector operably injects steam into the trapped vortex cavity and the steam mixes with the combustion gases.

公开(公告)号：US20240418369A1

公开(公告)日：2024-12-19

申请号：US18359178

申请日：2023-07-26

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Pradeep Naik ,  Clayton Stuart Cooper ,  Perumallu Vukanti ,  Michael A. Benjamin ,  Steven C. Vise ,  Sripathi Mohan ,  Ajoy Patra ,  Karthikeyan Sampath

IPC: F23R3/00 ,  F23R3/34 ,  F23R3/42

Abstract: A turbine engine with a compressor section, a combustion section, and a turbine section in serial flow arrangement along an engine centerline. The combustion section including a primary combustor liner having an inner liner and an outer liner. A dome wall and a dome inlet are located in the dome wall. At least one opening is located in the outer liner downstream from the dome inlet. A primary combustion chamber and a set of secondary combustors are fluidly coupled to the primary combustion chamber at the at least one opening.

公开(公告)号：US20240230099A9

公开(公告)日：2024-07-11

申请号：US18314414

申请日：2023-05-09

Applicant: General Electric Company

Inventor： Hiranya Nath ,  Ravindra Shankar Ganiger ,  Sripathi Mohan ,  Perumallu Vukanti ,  Kwanwoo Kim

IPC: F23R3/42

CPC classification number: F23R3/42 ,  F23R2900/00014

Abstract: A combustor for a turbomachine engine. The combustor includes a combustion chamber, and a cowl having an annular shape that is symmetric around a centerline axis of the turbomachine engine. The cowl includes a hollow cavity that is in fluid communication with the combustion chamber. The hollow cavity is a damper that reduces combustion dynamics of the combustor.

公开(公告)号：US20230258336A1

公开(公告)日：2023-08-17

申请号：US17806576

申请日：2022-06-13

Applicant: General Electric Company

Inventor： Ravindra Shankar Ganiger ,  Hiranya Nath ,  Sripathi Mohan

IPC: F23R3/00

CPC classification number: F23R3/002 ,  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.

公开(公告)号：US20250129748A1

公开(公告)日：2025-04-24

申请号：US18492002

申请日：2023-10-23

Applicant: General Electric Company

Inventor： Pradeep Naik ,  Clayton S. Cooper ,  Steven C. Vise ,  Michael A. Benjamin ,  Steven Marakovits ,  Sibtosh Pal ,  Sripathi Mohan

IPC: F02C3/30 ,  F02C9/28

Abstract: A turbine engine has a combustor in a core air flow path that generates combustion gases and a fuel and steam system fluidly coupled to the combustor. The fuel and steam system has a steam system to provide a steam flow to the combustor and a fuel system to provide a primary fuel flow and a secondary fuel flow to the combustor. The fuel system has a first state in which there is a first flow rate of the secondary fuel flow to the combustor and a second state in which there is a second flow rate of the secondary fuel flow to the combustor. The first flow rate and the second flow rate are different. The first state and the second state are based on a condition of the steam system.