公开(公告)号：US20240295323A1

公开(公告)日：2024-09-05

申请号：US18660388

申请日：2024-05-10

Applicant: General Electric Company

Inventor： Michael A. Benjamin ,  Manampathy G. Giridharan

IPC: F23R3/00 ,  F02C7/22 ,  F23R3/04

CPC classification number: F23R3/002 ,  F02C7/22 ,  F23R3/04

Abstract: A gas turbine engine includes a hydrogen fuel delivery assembly configured to deliver a hydrogen fuel flow, a compressor section configured to compress air flowing therethrough to provide a compressed air flow, and a combustor including a combustion chamber having a burner length and a burner dome height. The combustion chamber is configured to combust a mixture of the hydrogen fuel flow and the compressed air flow. The combustion chamber can be characterized by a combustor size rating between one inch and seven inches. In more detail, the combustion chamber can be characterized by the combustor size rating between one inch and seven inches at a core air flow parameter between two and one half kN and sixty kN, in which the combustor size rating is a function of the core air flow parameter.

公开(公告)号：US12018839B2

公开(公告)日：2024-06-25

申请号：US17969913

申请日：2022-10-20

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Pradeep Naik ,  Perumallu Vukanti ,  Michael T. Bucaro ,  Sibtosh Pal ,  Michael A. Benjamin ,  Bhavya Naidu Panduri ,  Aritra Chakraborty ,  Pabitra Badhuk

IPC: F02C7/22 ,  F23R3/00 ,  F23R3/28

CPC classification number: F23R3/28 ,  F02C7/22 ,  F23R3/002 ,  F05D2220/32 ,  F05D2240/35

Abstract: A combustor including an annular liner, a dome wall, a combustion chamber, at least one fuel cup and at least one dilution passage. The fuel cup being provided on the dome wall and being fluidly coupled to the combustion chamber. The fuel cup defining a fuel cup centerline. The at least on dilution passage terminating in at least on slot opening onto the dome wall, with the at least one slot having a longitudinal body axis.

公开(公告)号：US20240200777A1

公开(公告)日：2024-06-20

申请号：US18104433

申请日：2023-02-01

Applicant: GENERAL ELECTRIC COMPANY

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

IPC: F23R3/06 ,  F23R3/28

CPC classification number: F23R3/06 ,  F23R3/28

Abstract: A combustor comprising a dome wall, an annular liner, a combustion chamber, a set of fuel cups, and a set of dilution passages for each fuel cup of the set of fuel cups. The set of fuel cups circumferentially spaced along the dome wall relative to the combustor centerline. The set of dilution passages terminating in a plurality of slots spaced about the corresponding fuel cup in the set of fuel cups.

公开(公告)号：US11898755B2

公开(公告)日：2024-02-13

申请号：US17805983

申请日：2022-06-08

Applicant: General Electric Company

Inventor： Ravindra Shankar Ganiger ,  Hiranya Nath ,  Michael A. Benjamin ,  Nicholas R. Overman

IPC: F23R3/34 ,  F23R3/26 ,  F23R3/00

CPC classification number: F23R3/346 ,  F23R3/002 ,  F23R3/26 ,  F23R2900/00014 ,  F23R2900/03044

Abstract: A combustor for a gas turbine has a combustor liner including an outer liner and an inner liner, a combustion chamber being defined between the outer liner and the inner liner. The combustion chamber includes a primary combustion zone at an upstream end of the combustion chamber. The combustor also includes an outer liner expanded primary volume portion, and a secondary outer liner portion. One of the outer liner expanded primary volume portion and the secondary outer liner portion is movable to adjust a volume of the primary combustion zone by opening and closing access to the outer liner expanded primary volume portion so as to increase and to decrease the volume of the primary combustion zone.

公开(公告)号：US20230366551A1

公开(公告)日：2023-11-16

申请号：US18350205

申请日：2023-07-11

Applicant: General Electric Company

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

IPC: F23R3/14 ,  F23R3/28

CPC classification number: F23R3/14 ,  F23R3/286

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, which can supply a primary fuel supply and a secondary fuel supply. Increasing efficiency and reducing emission require the use of alternative fuels, which combust at higher temperatures or burn at faster burn speeds than traditional fuels, requiring improved fuel introduction without the occurrence of flame holding or flashback.

公开(公告)号：US11795879B2

公开(公告)日：2023-10-24

申请号：US17589145

申请日：2022-01-31

Applicant: General Electric Company

Inventor： Krishnakumar Venkatesan ,  Michael A. Benjamin ,  Michael T. Bucaro

IPC: F02C7/266 ,  F23R3/28 ,  F02C7/232

CPC classification number: F02C7/266 ,  F23R3/286 ,  F02C7/232 ,  F23R3/28 ,  F23R2900/00006 ,  F23R2900/00009

Abstract: A turbine engine comprising a compressor section, a combustion section having a combustor, and a turbine section in serial flow arrangement. The combustor having a combustion chamber, at least one fuel injector, at least one compressed air passage, and at least one igniter. The at least one igniter can be provided within a portion of the at least one fuel injector or the at least one compressed air passage.

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：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.