公开(公告)号：US20250067214A1

公开(公告)日：2025-02-27

申请号：US18501484

申请日：2023-11-03

Applicant: General Electric Company

Inventor： Perumallu Vukanti ,  Pradeep Naik ,  Saket Singh ,  Michael A. Benjamin ,  Sripathi Mohan ,  Clayton S. Cooper ,  Rajendra Wankhade ,  Hiranya Nath ,  Nicholas R. Overman ,  Steven C. Vise

IPC: F02C3/30 ,  F23R3/04

Abstract: A combustor includes a combustion chamber and an annular dome. The combustion chamber includes an outer liner and an inner liner and has a combustion zone. The annular dome is coupled to the outer liner and the inner liner. A plurality of mixing assemblies operably injects a fuel-air mixture into the combustion zone of the combustion chamber to produce combustion gases. A combustor steam system is in fluid communication with the combustion chamber. The combustor steam system includes a steam path defined by at least one of the outer liner, the inner liner, or the annular dome. The combustor steam system operably directs steam through the steam path from the at least one of the outer liner, the inner liner, or the annular dome and into 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：US12196422B2

公开(公告)日：2025-01-14

申请号：US17664971

申请日：2022-05-25

Applicant: General Electric Company

Inventor： Saket Singh ,  Rimple Rangrej ,  Pradeep Naik ,  Michael A. Benjamin ,  Joseph Zelina

IPC: F23R3/34 ,  F23R3/06

Abstract: A combustor for a gas turbine includes a combustor liner having an outer liner and an inner liner defining a combustion chamber therebetween. At least one of the outer liner and the inner liner includes a dilution fence arranged in a dilution zone of the combustion chamber. The dilution fence extends into the combustion chamber and has at least one secondary fuel nozzle opening therethrough, and at least one secondary fuel nozzle is arranged through the at least one secondary fuel nozzle opening.

公开(公告)号：US20240410586A1

公开(公告)日：2024-12-12

申请号：US18808558

申请日：2024-08-19

Applicant: General Electric Company

Inventor： Ravindra Shankar Ganiger ,  Hiranya Kumar Nath ,  Daniel J. Kirtley ,  Shai Birmaher ,  Veeraraju Vanapalli ,  Karthikeyan Sampath ,  Deepak Ghiya ,  Perumallu Vukanti ,  Rajendra Mahadeorao Wankhade ,  Pradeep Naik ,  Rimple Rakeshkumar Rangrej ,  Saket Singh

IPC: F23R3/42 ,  F02C3/02 ,  F02C3/14

Abstract: A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor including: a forward liner segment; and an aft liner segment disposed downstream from the forward liner segment relative to a direction of flow through the combustor, the forward and aft liner segments at least partially defining a combustion chamber, wherein the forward and aft liner segments are coupled together at a moveable interface.

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.

公开(公告)号：US12111057B2

公开(公告)日：2024-10-08

申请号：US18320682

申请日：2023-05-19

Applicant: General Electric Company

Inventor： Pradeep Naik ,  Manampathy G. Giridharan ,  Vishal Sanjay Kediya ,  Gregory A. Boardman

IPC: F23R3/28 ,  F02C3/20 ,  F23R3/12 ,  F23R3/34 ,  F23R3/36 ,  F02C7/22 ,  F02C7/26

CPC classification number: F23R3/286 ,  F23R3/12 ,  F23R3/343 ,  F02C3/20 ,  F02C7/222 ,  F02C7/26 ,  F23R3/36

Abstract: A mixer for blending fuel and air in a combustor of a turbine engine. The mixer includes a central body having a central passageway and a central axis. The mixer includes a plurality of tubes positioned radially around the central axis and circumferentially around a periphery of the mixer. Each of the tubes of the mixer includes opposed openings and a tangential opening. Each of the tubes of the mixer includes a cylindrical interior mixing passage configured to receive air flow from the opposed openings and the tangential opening and a fuel flow. The opposed openings are configured to spread the fuel flow laterally and the tangential opening is configured to spread the fuel flow tangentially.

公开(公告)号：US20240318821A1

公开(公告)日：2024-09-26

申请号：US18186518

申请日：2023-03-20

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Manampathy G. Giridharan ,  Pradeep Naik ,  Michael A. Benjamin

IPC: F23R3/06

CPC classification number: F23R3/06 ,  F23R3/26

Abstract: A combustor having a casing, an inner liner, an outer liner, a compressed air passageway, a combustion chamber and at least one dilution passage. The compressed air passageway being formed between the casing, the inner liner and the outer liner. The combustion chamber being at least partially defined by the inner liner and the outer liner. The at least one dilution passage extending through at least one of the inner liner or the outer liner. The at least one dilution passage extending between an inlet fluidly coupled to the compressed air passageway and a dilution hole fluidly coupled to the combustion chamber.

公开(公告)号：US12092332B2

公开(公告)日：2024-09-17

申请号：US17675270

申请日：2022-02-18

Applicant: General Electric Company

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

IPC: F23R3/28 ,  F02C7/22 ,  F23C7/00 ,  F23D17/00 ,  F23L7/00 ,  F23R3/14 ,  F23R3/36

CPC classification number: F23R3/286 ,  F02C7/22 ,  F23C7/004 ,  F23D17/002 ,  F23L7/002 ,  F23R3/14 ,  F23R3/36

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. The fuel nozzle assembly can be configured to increase lateral provision of fuels to reduce flame scrubbing on combustor liners for the combustor.

公开(公告)号：US20240280264A1

公开(公告)日：2024-08-22

申请号：US18296220

申请日：2023-04-05

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Bhavya Naidu Panduri ,  Perumallu Vukanti ,  Pradeep Naik ,  Michael T. Bucaro ,  Sibtosh Pal ,  Aritra Chakraborty ,  Pabitra Badhuk ,  Arijit Sinha Roy ,  Ajoy Patra ,  R Narasimha Chiranthan

IPC: F23R3/00

CPC classification number: F23R3/06 ,  F23R3/002

Abstract: A combustor for a gas turbine engine. The combustor having a dome wall, a set of fuel cups, an inner liner, an outer liner, and a set of dilution passages. The dome wall, the inner liner, and the outer liner, together, at least partially defining a combustion chamber. The set of dilution passages terminating in a plurality of dilution holes arranged in a dilution hole arrangement provided in at least one of the inner liner or the outer liner. The dilution hole arrangement having at least a first subset of dilution holes arranged along a first leg and a second subset of dilution holes arranged along a second leg.