公开(公告)号：US20250035311A1

公开(公告)日：2025-01-30

申请号：US18804465

申请日：2024-08-14

Applicant: General Electric Company

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

IPC: F23R3/28 ,  F02C7/22 ,  F23C7/00 ,  F23D17/00 ,  F23L7/00 ,  F23R3/14 ,  F23R3/36

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. The fuel nozzle assembly can be configured to increase lateral provision of fuels to reduce flame scrubbing on combustor liners for the combustor.

公开(公告)号：US20240328622A1

公开(公告)日：2024-10-03

申请号：US18736704

申请日：2024-06-07

Applicant: General Electric Company

Inventor： Michael A. Benjamin ,  Manampathy G. Giridharan

IPC: F23R3/00 ,  F02C7/22 ,  F23R3/28

CPC classification number: F23R3/002 ,  F02C7/22 ,  F23R3/28 ,  F05D2220/323

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：US20240309805A1

公开(公告)日：2024-09-19

申请号：US18673577

申请日：2024-05-24

Applicant: General Electric Company

Inventor： Michael A. Benjamin ,  Manampathy G. Giridharan

IPC: F02C3/22 ,  F02C7/22 ,  F23R3/00 ,  F23R3/28

CPC classification number: F02C3/22 ,  F02C7/22 ,  F23R3/002 ,  F23R3/286 ,  F05D2220/323 ,  F05D2240/35

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：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：US20240102656A1

公开(公告)日：2024-03-28

申请号：US18529360

申请日：2023-12-05

Applicant: General Electric Company

Inventor： Manampathy G. Giridharan ,  Pradeep Naik

IPC: F23R3/34 ,  F02C3/20 ,  F02C3/30 ,  F23R3/36

CPC classification number: F23R3/346 ,  F02C3/20 ,  F02C3/30 ,  F23R3/36 ,  F23R3/002 ,  F23R3/34

Abstract: A gas turbine engine including a compressor section, a combustor for combusting a fuel, and a turbine. Compressed air flows through a combustion liner of the combustor in a bulk airflow direction. The combustor includes a primary fuel nozzle and a secondary fuel nozzle. The secondary fuel nozzle is downstream of the primary fuel nozzle in the bulk airflow direction. The primary fuel nozzle is configured to inject a primary portion of the fuel into a primary combustion zone, and the secondary fuel nozzle is configured to inject a secondary portion of the fuel into a secondary combustion zone. The secondary combustion zone is located downstream of the primary combustion zone in the bulk airflow direction. The fuel may be one of diatomic hydrogen fuel and a hydrogen enriched fuel.

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：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：US20230213194A1

公开(公告)日：2023-07-06

申请号：US17699735

申请日：2022-03-21

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Pradeep Naik ,  Manampathy G. Giridharan ,  Ajoy Patra ,  R Narasimha Chiranthan

IPC: F23R3/28 ,  F23R3/14

CPC classification number: F23R3/286 ,  F23R3/14 ,  F23R2900/03042

Abstract: A turbine engine can include a compressor section, a combustion section, and a turbine section in serial flow arrangement. The combustion section can include a combustor with a fuel premixer. The fuel premixer can include an annular shroud defining an interior, a center body located within the interior, and an annular swirler located within the interior.

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：US11692709B2

公开(公告)日：2023-07-04

申请号：US17199257

申请日：2021-03-11

Applicant: General Electric Company

Inventor： Pradeep Naik ,  Manampathy G. Giridharan ,  Vishal Sanjay Kediya ,  Gregory A. Boardman

IPC: F23R3/28 ,  F23R3/12 ,  F23R3/34 ,  F02C7/22

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.