公开(公告)号：US12222104B2

公开(公告)日：2025-02-11

申请号：US17740443

申请日：2022-05-10

Applicant: General Electric Company

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

IPC: F23R3/00 ,  F23R3/16 ,  F23R3/26

Abstract: A turbine engine can include a compressor section, a combustion section, and a turbine section in serial flow arrangement. A combustor in the combustion section can include a combustor liner at least partially defining a combustion chamber. The combustor liner can include at least one aperture fluidly coupled to the combustion chamber.

公开(公告)号：US20250035304A1

公开(公告)日：2025-01-30

申请号：US18913347

申请日：2024-10-11

Applicant: General Electric Company

Inventor： Steven C. Vise ,  Clayton S. Cooper ,  Michael A. Benjamin ,  Pradeep Naik ,  Kwanwoo Kim ,  Shai Birmaher ,  Perumallu Vukanti ,  Saket Singh ,  Karthikeyan Sampath

IPC: F23D11/38 ,  B05B7/10

Abstract: A swirler-ferrule assembly includes a radial swirler, a ferrule, a fuel nozzle, and a surface feature. The radial swirler includes a primary swirler vane having a primary air passage and a secondary swirler vane having a secondary air passage. The ferrule may be connected to the radial swirler. The surface feature may be located on the primary swirler vane and/or the ferrule. The surface feature may be configured to direct an air flow through the primary air passage away from a recirculation zone located upstream of the primary swirler vane. The surface feature has a trailing end and a distal end, and the fuel nozzle is axially aligned with the trailing end of the surface feature or is located axially downstream of the trailing end of the surface feature. The surface feature may have a plurality of grooves.

公开(公告)号：US12173898B1

公开(公告)日：2024-12-24

申请号：US18486368

申请日：2023-10-13

Applicant: GENERAL ELECTRIC COMPANY

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

IPC: F23R3/00 ,  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. A combustion section for the turbine engine, having a primary combustor liner including an inner liner and an outer liner annular about an engine centerline. A dome wall extending between the inner liner and the outer liner. A set of primary dome inlets located in the dome wall and circumferentially arranged about the engine centerline. A set of secondary combustors fluidly coupled to a primary combustion chamber, the set of secondary combustors including a first mini combustor and a second mini combustor.

公开(公告)号：US12163660B2

公开(公告)日：2024-12-10

申请号：US18484987

申请日：2023-10-11

Applicant: General Electric Company

Inventor： Rimple Rangrej ,  Saket Singh ,  Pradeep Naik ,  Ajoy Patra

IPC: F23R3/06

Abstract: A combustor for a turbomachine engine includes a combustion chamber, a liner forming a boundary of the combustion chamber, and multiple dilution holes through the liner to permit airflow into the combustion chamber. The dilution holes include converging dilution holes and diverging dilution holes, the converging dilution holes having a converging cross-sectional profile and the diverging dilution holes having a diverging cross-sectional profile.

公开(公告)号：US20240401527A1

公开(公告)日：2024-12-05

申请号：US18497199

申请日：2023-10-30

Applicant: General Electric Company

Inventor： Pradeep Naik ,  Sibtosh Pal ,  Saket Singh

IPC: F02C7/04

Abstract: A gas turbine includes a combustion section, and a diffuser arranged to provide a flow of compressed air from a compressor to the combustion section. The diffuser includes a steam injection system that provides a flow of steam from the diffuser to the combustion section.

公开(公告)号：US20240328360A1

公开(公告)日：2024-10-03

申请号：US18742260

申请日：2024-06-13

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：US20240318822A1

公开(公告)日：2024-09-26

申请号：US18663324

申请日：2024-05-14

Applicant: General Electric Company

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

IPC: F23R3/06

CPC classification number: F23R3/06

Abstract: A gas turbine engine includes a compressor section, a combustor section, and a turbine section in fore-to-aft serial flow arrangement and defines an engine centerline. The combustor section includes a combustor liner at least partially defining a combustor chamber and a dome wall, coupled to the combustor liner, and defining a forward end of the combustion chamber. A fuel nozzle is located on the dome wall and fluidly coupled to the combustion chamber. A first set of compressed air openings emit compressed air into the combustion chamber along a first flow path and a second set of compressed air openings emit compressed air into the combustion chamber along a second flow path. The first and second flow paths intersect at an intersection point to form a sheet of air.

公开(公告)号：US20240247807A1

公开(公告)日：2024-07-25

申请号：US18585509

申请日：2024-02-23

Applicant: General Electric Company

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

IPC: F23R3/60 ,  B33Y80/00 ,  F23R3/06

CPC classification number: F23R3/60 ,  F23R3/06 ,  B33Y80/00 ,  F23R2900/00012 ,  F23R2900/00017 ,  F23R2900/00018

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; 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; and an intermediate member disposed at least partially between the forward and aft liner segments and extending in the circumferential direction.

公开(公告)号：US11920790B2

公开(公告)日：2024-03-05

申请号：US17649220

申请日：2022-01-28

Applicant: General Electric Company

Inventor： Saket Singh ,  Pradeep Naik ,  Rimple Rangrej ,  Ranganatha Narasimha Chiranthan ,  Krishnendu Chakraborty ,  Shai Birmaher

IPC: F23R3/00 ,  F23R3/06

CPC classification number: F23R3/002 ,  F23R3/06

Abstract: A combustor liner for a combustor of a gas turbine includes an outer liner having a plurality of outer liner segments, and an inner liner having a plurality of inner liner segments. Each segment of the inner liner and the outer liner includes at least one slotted dilution opening therethrough extending in a circumferential direction, and each slotted dilution opening includes a deflector wall extending radially from the respective liner into a dilution zone of a combustion chamber between the outer liner and the inner liner. The at least one slotted dilution opening may be a curved slot (either concave or convex) dilution opening, and the curved slot dilution openings for each segment of the outer liner and the inner liner may be connected so as to provide a wavy slotted dilution opening extending annularly through the outer liner and the inner liner.

公开(公告)号：US20240044493A1

公开(公告)日：2024-02-08

申请号：US18484987

申请日：2023-10-11

Applicant: General Electric Company

Inventor： Rimple Rangrej ,  Saket Singh ,  Pradeep Naik ,  Ajoy Patra

IPC: F23R3/06

CPC classification number: F23R3/06

Abstract: A combustor for a turbomachine engine includes a combustion chamber, a liner forming a boundary of the combustion chamber, and multiple dilution holes through the liner to permit airflow into the combustion chamber. The dilution holes include converging dilution holes and diverging dilution holes, the converging dilution holes having a converging cross-sectional profile and the diverging dilution holes having a diverging cross-sectional profile.