公开(公告)号：US20230288065A1

公开(公告)日：2023-09-14

申请号：US17810678

申请日：2022-07-05

Applicant: General Electric Company

Inventor： Saket Singh ,  Ravindra Shankar Ganiger ,  Hiranya Nath ,  Perumallu Vukanti ,  Ajoy Patra ,  Karthikeyan Sampath ,  Pradeep Naik ,  Rimple Rangrej ,  Veera Venkata Amarnath Manem

IPC: F23R3/00 ,  F23R3/60

CPC classification number: F23R3/002 ,  F23R3/60 ,  F23R2900/00017 ,  F23R2900/03043

Abstract: A dome-deflector assembly for a gas turbine includes a dome, a deflector, and at least one dome-deflector connecting assembly that includes a connecting member connecting the dome and the deflector together with a cavity being defined between the dome and the deflector. The connecting member extends through the deflector and has a first end arranged at a hot surface side of the deflector and a second end arranged to connect with the dome. The dome-deflector connecting assembly is configured to provide a flow of cooling air from the cavity to the hot surface side of the deflector to cool the first end of the connecting member on the hot surface side of the deflector.

公开(公告)号：US20230266002A1

公开(公告)日：2023-08-24

申请号：US17651644

申请日：2022-02-18

Applicant: General Electric Company

Inventor： Pradeep Naik ,  Shai Birmaher ,  Kwanwoo Kim ,  Saket Singh ,  Perumallu Vukanti ,  Karthikeyan Sampath ,  Steven C. Vise ,  Nicholas R. Overman ,  Michael A. Benjamin

IPC: F23D11/38 ,  F23R3/14 ,  F23R3/28 ,  F23R3/50

CPC classification number: F23D11/383 ,  F23R3/14 ,  F23R3/283 ,  F23R3/286 ,  F23R3/50 ,  F23R2900/03041 ,  F23R2900/03042

Abstract: A swirler assembly includes a swirler having a primary swirler with a primary swirler venturi, a swirler ferrule plate connected upstream to the primary swirler, and a fuel nozzle disposed in the swirler ferrule plate. The swirler ferrule plate has an annular pressure drop cavity with oxidizer inlet orifices in fluid communication with the swirler, and at least one outlet orifice in fluid communication with the primary swirler venturi. A second flow of oxidizer to the swirler incurs a first pressure drop, a third flow of the oxidizer from the swirler to the annular pressure drop cavity incurs a second pressure drop, and a fourth flow of the oxidizer from the annular pressure drop cavity to the primary swirler venturi incurs a third pressure drop.

公开(公告)号：US20230235884A1

公开(公告)日：2023-07-27

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

CPC classification number: F23R3/002 ,  F02C3/04 ,  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：US20230212984A1

公开(公告)日：2023-07-06

申请号：US17692411

申请日：2022-03-11

Applicant: GENERAL ELECTRIC COMPANY

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

IPC: F02C7/232 ,  F23R3/28

CPC classification number: F02C7/232 ,  F23R3/28 ,  F05D2220/32 ,  F05D2240/35

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. Varying the geometry of the swirler can provide for improved supply of air, which can improve efficiency and flame control.

公开(公告)号：US20230194088A1

公开(公告)日：2023-06-22

申请号：US17686800

申请日：2022-03-04

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

CPC classification number: F23R3/06 ,  F23R3/286 ,  F23R2900/03044

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：US11649966B1

公开(公告)日：2023-05-16

申请号：US17689070

申请日：2022-03-08

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 ,  F23R3/04 ,  F23R3/50 ,  F23D14/64

CPC classification number: F23R3/286 ,  F02C7/264 ,  F23D14/64 ,  F23R3/045 ,  F23R3/50 ,  F05D2240/35 ,  F05D2260/99 ,  F23D2207/00

Abstract: A turbine engine having a combustion section. The combustion section can have a combustor, at least one fuel cup, and at least one ignition tube. The combustor can include a combustor liner and a dome wall, which together at least partially define a combustion chamber. The at least one fuel cup can include a swirler and a fuel injector. The at least one ignition tube can include an outlet directly fluidly coupled to the combustion chamber.

公开(公告)号：US20220412550A1

公开(公告)日：2022-12-29

申请号：US17396155

申请日：2021-08-06

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：US11268438B2

公开(公告)日：2022-03-08

申请号：US15705314

申请日：2017-09-15

Applicant: General Electric Company

Inventor： Steven Clayton Vise ,  Allen Michael Danis ,  Jayanth Sekar ,  Pradeep Naik ,  Perumallu Vukanti ,  Arthur Wesley Johnson ,  Clayton Stuart Cooper ,  Karthikeyan Sampath

IPC: F02C3/22 ,  F23R3/00 ,  F23R3/04 ,  F23R3/06 ,  F23R3/16

Abstract: An apparatus and method for a combustor, the combustor including combustor liner having a plurality of dilution openings. The combustor receives a flow of fuel that is ignited and mixed with dilution air to form a flow of combustion gases. The flow of combustion gases travels through the combustor to a turbine section of an engine.

公开(公告)号：US11226101B2

公开(公告)日：2022-01-18

申请号：US16264775

申请日：2019-02-01

Applicant: General Electric Company

Inventor： Karthikeyan Sampath ,  Saket Singh ,  Gurunath Gandikota ,  Perumallu Vukanti ,  Pradeep Naik ,  Steven Clayton Vise

IPC: F23R3/14 ,  F23R3/28

Abstract: A gas turbine engine swirler that includes a tubular body having a forward face, an aft end, and a throat. A plurality of primary swirl vanes that is positioned between the aft end and the forward face. A plurality of secondary swirl vanes that is positioned between the primary swirl vanes and the aft end. The plurality of primary swirl vanes and the plurality of secondary swirl vanes are configured such that the throat is fluidly connected to a plenum that is positioned outside of the tubular body. A tubular ferrule is positioned such that it joins the body at the forward face thereof. Each of the primary swirl vanes extend radially inwardly to a vane lip. The secondary swirl vanes extend radially inwardly for swirling air therefrom. The body also includes a tubular Venturi that extends aft from between the primary swirler vanes and the secondary swirler vanes for radially separating air swirled therefrom. Wherein the primary swirl vanes are configured to swirl air along a passageway and through an outlet that is oriented axially aft.

公开(公告)号：US20210278085A1

公开(公告)日：2021-09-09

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: F23R3/28 ,  F02C7/22 ,  F23R3/00

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.