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.

公开(公告)号：US20230408093A1

公开(公告)日：2023-12-21

申请号：US18460078

申请日：2023-09-01

Applicant: General Electric Company

Inventor： Gurunath Gandikota ,  Karthikeyan Sampath ,  Perumallu Vukanti ,  Allen M. Danis ,  Scott M. Bush ,  Steven Clayton Vise ,  Hari Ravi Chandra ,  Rimple Rangrej ,  Saket Singh ,  Pradeep Naik ,  Neeraj Kumar Mishra ,  Arvind Kumar Rao ,  Balasubramaniam Venkatanarayanan ,  Ranjeet Kumar Mishra

IPC: F23R3/14 ,  F23R3/28

CPC classification number: F23R3/14 ,  F23R3/286

Abstract: A swirler assembly for a combustor includes at least one swirler including a plurality of swirl vanes arrayed about an axis of the swirler. The plurality of swirl vanes includes a first ring of first sub-vanes and a second ring of second sub-vanes, the first ring of first sub-vanes and the second ring of second sub-vanes being separated by a gap therebetween.

公开(公告)号：US11828465B2

公开(公告)日：2023-11-28

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 ,  F23R3/28

CPC classification number: F23R3/002 ,  F02C3/04 ,  F23R3/286 ,  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：US20230313996A1

公开(公告)日：2023-10-05

申请号：US17811762

申请日：2022-07-11

Applicant: General Electric Company

Inventor： Ranganatha Narasimha Chiranthan ,  Karthikeyan Sampath ,  Perumallu Vukanti ,  Pradeep Naik

IPC: F23R3/42 ,  F02C3/14 ,  F02C7/00

CPC classification number: F23R3/42 ,  F02C7/00 ,  F02C3/14

Abstract: An annular dome assembly for a combustor. The annular dome assembly includes an annular dome including one or more dome panels defining the annular dome. A first dome panel includes a dome upstream surface and a dome downstream surface opposite the dome upstream surface. One or more dome arms extend from the dome upstream surface. One or more apertures extend from the dome upstream surface to the dome downstream surface. The annular dome assembly also includes a deflector assembly including one or more deflector panels defining the deflector assembly. A first deflector panel includes a deflector upstream surface and a deflector downstream surface opposite the deflector upstream surface. One or more deflector arms extend from the deflector upstream surface. Each of the one or more deflector arms are mounted within a respective aperture of the annular dome.

公开(公告)号：US20230288069A1

公开(公告)日：2023-09-14

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 ,  F23R3/12 ,  F23R3/34

CPC classification number: F23R3/286 ,  F23R3/12 ,  F23R3/343 ,  F02C7/222

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：US20230288066A1

公开(公告)日：2023-09-14

申请号：US18320529

申请日：2023-05-19

Applicant: General Electric Company

Inventor： Pradeep Naik ,  Shai Birmaher ,  Saket Singh ,  Krishnendu Chakraborty

IPC: F23R3/06 ,  F23R3/04 ,  F23R3/00

CPC classification number: F23R3/06 ,  F23R3/045 ,  F23R3/002 ,  F23R2900/03043

Abstract: A liner for a combustor in a gas turbine engine and a related method. The liner includes a liner body having a cold side and a hot side. The liner includes a dilution array having a plurality of dilution passages, each dilution passage of the plurality of dilution passages having a concatenated geometry repeating in a predetermined pattern and extending circumferentially around the liner body. The dilution passage integrates a first dilution air flow flowing through the dilution passage from the cold side to the hot side and a second dilution air flow flowing through the dilution passage from the cold side to the hot side into an integrated dilution air flow and injects the integrated dilution air flow into a core primary combustion zone of the combustor to attain a predetermined combustion state of the combustor. The dilution array is repeated along an axial length of the liner body.