公开(公告)号：US12241628B2

公开(公告)日：2025-03-04

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

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：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：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：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：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：US11635209B2

公开(公告)日：2023-04-25

申请号：US17649128

申请日：2022-01-27

Applicant: General Electric Company

Inventor： Perumallu Vukanti ,  Pradeep Naik ,  Sripathi Mohan ,  Karthikeyan Sampath ,  Steven C. Vise ,  Shai Birmaher ,  Saket Singh

IPC: F23R3/14 ,  F23R3/28 ,  F23R3/16

Abstract: A swirler assembly includes a swirler having a primary swirler and a secondary swirler, and a flare connected the secondary swirler, and a dome disposed radially outward of the flare. A flare oxidizer flow passage is defined by a flare outer surface and a dome inner surface, and the flare oxidizer flow passage includes a swirl inducing member therewithin that induces a swirled flow of an oxidizer passing through the flare oxidizer flow passage into a combustion chamber.

公开(公告)号：US20230053389A1

公开(公告)日：2023-02-23

申请号：US17649128

申请日：2022-01-27

Applicant: General Electric Company

Inventor： Perumallu Vukanti ,  Pradeep Naik ,  Sripathi Mohan ,  Karthikeyan Sampath ,  Steven C. Vise ,  Shai Birmaher ,  Saket Singh

IPC: F23R3/16 ,  F23R3/28

Abstract: A swirler assembly includes a swirler having a primary swirler and a secondary swirler, and a flare connected the secondary swirler, and a dome disposed radially outward of the flare. A flare oxidizer flow passage is defined by a flare outer surface and a dome inner surface, and the flare oxidizer flow passage includes a swirl inducing member therewithin that induces a swirled flow of an oxidizer passing through the flare oxidizer flow passage into a combustion chamber.

公开(公告)号：US11280495B2

公开(公告)日：2022-03-22

申请号：US16808443

申请日：2020-03-04

Applicant: General Electric Company

Inventor： Gurunath Gandikota ,  Steven Clayton Vise ,  Perumallu Vukanti ,  Mayank Krisna Amble ,  Clayton Stuart Cooper ,  Nicholas Ryan Overman ,  Karthikeyan Sampath ,  Allen Michael Danis ,  Craig Douglas Young

IPC: F23R3/14 ,  F23R3/28 ,  F23R3/00 ,  F02C7/22

Abstract: A flow device for a combustor assembly defining a longitudinal axis around which the flow device is positioned is provided. The flow device includes a body extended around the longitudinal axis. The body includes a first wall and a second wall separated longitudinally from one another along the longitudinal axis. A fuel injector passage is defined through the body coaxial to the longitudinal axis. A plurality of vane walls is extended radially between the first wall and the second wall relative to the longitudinal axis. A radial flow passage is extended between the plurality of vane walls and the fuel injector passage.

公开(公告)号：US11175045B2

公开(公告)日：2021-11-16

申请号：US15861791

申请日：2018-01-04

Applicant: General Electric Company

Inventor： Michael Anthony Benjamin ,  Girish Venkata Satya Sesha Goda ,  Habeeb Kunnummal Manat ,  Karthikeyan Sampath

IPC: F23R3/28 ,  F23R3/10 ,  F23R3/18 ,  F23R3/14 ,  F23C7/00 ,  F23R3/34

Abstract: A method and structure for operating a combustion system of a gas turbine engine to mitigate low frequency combustion acoustics is generally provided. The method includes flowing an oxidizer through a fuel nozzle passage defining an inner wall and an outer wall, in which each of the inner wall and the outer wall are contoured from a first radius to a second radius smaller than the first radius; flowing the oxidizer at a higher axial velocity at the inner wall relative to the outer wall upstream of a fuel injection port; flowing a fuel through the fuel injection port to the fuel nozzle passage to mix with the flow of oxidizer to produce a fuel-oxidizer mixture; and igniting the fuel-oxidizer mixture downstream of the fuel injection port.