公开(公告)号：US12241424B2

公开(公告)日：2025-03-04

申请号：US17209724

申请日：2021-03-23

Applicant: General Electric Company

Inventor： Arthur W. Sibbach ,  Paul Burchell Glaser ,  Michael A. Benjamin

IPC: F02C9/46 ,  B64D37/32 ,  F01D21/00 ,  F01D21/12 ,  F02C7/22

Abstract: A fuel leak detection system for hydrogen fuel system including a monitored component. The fuel leak detection system including a sensor and controller communicatively coupled to the sensor. The sensor is positioned to monitor at least a portion of the monitored component. The sensor is configured (i) to sense a parameter corresponding to a hydrogen fuel leak of the monitored component and (ii) to generate an output. The controller is configured (i) to receive the output of the sensor, (ii) to determine, based on the output of the sensor, if a leak has occurred in the monitored component, and (iii) to generate an output indicating a fuel system leak when the controller determines that the leak has occurred in the monitored component. The monitored component may be a component of one of a fuel tank, a power generator, and a fuel delivery assembly.

公开(公告)号：US20250067439A1

公开(公告)日：2025-02-27

申请号：US18453506

申请日：2023-08-22

Applicant: General Electric Company

Inventor： Pradeep Naik ,  Clayton S. Cooper ,  Perumallu Vukanti ,  Michael A. Benjamin ,  Steven C. Vise ,  Sripathi Mohan

IPC: F23R3/28

Abstract: A combustor includes a combustion chamber having an outer liner and an inner liner and defining a first combustion zone, an annular dome coupled to the outer liner and the inner liner, and a trapped vortex cavity extending from at least one of the outer liner or the inner liner and defining a second combustion zone. A plurality of first mixing assemblies are disposed through the annular dome, and operably inject a first fuel-air mixture into the first combustion zone. A plurality of second mixing assemblies are disposed at the trapped vortex cavity, and operably inject a second fuel-air mixture into the second combustion zone defined in the trapped vortex cavity to produce combustion gases. A steam system includes a steam injector in fluid communication with the trapped vortex cavity. The steam injector operably injects steam into the trapped vortex cavity and the steam mixes with the combustion gases.

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：US20240418369A1

公开(公告)日：2024-12-19

申请号：US18359178

申请日：2023-07-26

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Pradeep Naik ,  Clayton Stuart Cooper ,  Perumallu Vukanti ,  Michael A. Benjamin ,  Steven C. Vise ,  Sripathi Mohan ,  Ajoy Patra ,  Karthikeyan Sampath

IPC: F23R3/00 ,  F23R3/34 ,  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. The combustion section including a primary combustor liner having an inner liner and an outer liner. A dome wall and a dome inlet are located in the dome wall. At least one opening is located in the outer liner downstream from the dome inlet. A primary combustion chamber and a set of secondary combustors are fluidly coupled to the primary combustion chamber at the at least one opening.

公开(公告)号：US12130013B2

公开(公告)日：2024-10-29

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

CPC classification number: F23D11/383 ,  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：US12116935B2

公开(公告)日：2024-10-15

申请号：US18310386

申请日：2023-05-01

Applicant: General Electric Company

Inventor： Brandon W. Miller ,  Robert Jon McQuiston ,  Stefan Joseph Cafaro ,  Eric Richard Westervelt ,  Michael A. Benjamin ,  Joel M. Haynes ,  Hejie Li

IPC: F02C7/22 ,  F02C7/224 ,  F02C9/28

CPC classification number: F02C7/22 ,  F02C7/224 ,  F02C9/28 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2260/20

Abstract: A gas turbine engine fuel supply system can include a fuel delivery system, a thermal management system, a fuel manifold, and one or more sensors that identify one or more fuel parameters. A fuel control system adjusts parameters of the fuel based on data received from the sensors.

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：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.