公开(公告)号：US12196422B2

公开(公告)日：2025-01-14

申请号：US17664971

申请日：2022-05-25

Applicant: General Electric Company

Inventor： Saket Singh ,  Rimple Rangrej ,  Pradeep Naik ,  Michael A. Benjamin ,  Joseph Zelina

IPC: F23R3/34 ,  F23R3/06

Abstract: A combustor for a gas turbine includes a combustor liner having an outer liner and an inner liner defining a combustion chamber therebetween. At least one of the outer liner and the inner liner includes a dilution fence arranged in a dilution zone of the combustion chamber. The dilution fence extends into the combustion chamber and has at least one secondary fuel nozzle opening therethrough, and at least one secondary fuel nozzle is arranged through the at least one secondary fuel nozzle opening.

公开(公告)号：US20240401811A1

公开(公告)日：2024-12-05

申请号：US18326639

申请日：2023-05-31

Applicant: General Electric Company

Inventor： Hiranya Nath ,  Clayton S. Cooper ,  Richard W. Stickles ,  Michael A. Benjamin ,  Dharmaraj Pachaiappan ,  Ranganatha Narasimha Chiranthan ,  Sripathi Mohan

IPC: F23R3/28 ,  F02C9/44

Abstract: A combustor for a turbine engine includes a combustion chamber including an outer liner and an inner liner, and an annular dome. A plurality of first mixing assemblies includes a pilot mixer and a first main mixer, the first mixing assemblies disposed through the annular dome. The pilot mixer injects a pilot mixer fuel-air mixture axially into a first combustion zone, and the first main mixer injects a first main mixer fuel-air mixture radially into the first combustion zone. A plurality of second mixing assemblies includes a second main mixer, the second mixing assemblies being axially aft of the plurality of first mixing assemblies. The second main mixer injects a second main mixer fuel-air mixture radially into a second combustion zone that is axially aft of, and separate from, the first combustion zone.

公开(公告)号：US12152780B2

公开(公告)日：2024-11-26

申请号：US18302346

申请日：2023-04-18

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 ,  F23D14/64 ,  F23R3/04 ,  F23R3/50

Abstract: A method of supplying a first fuel and air mixture and a second fuel and air mixture to a combustor. The combustor having a combustion chamber, a dome wall at least partially defining the combustion chamber, at least one fuel cup provided in the dome wall, and at least one ignition tube having an outlet exhausting to the combustion chamber. The method comprising supplying a first flow of compressed air to only the at least one ignition tube, igniting the first fuel and air mixture, supplying the first ignited fuel and air mixture of the combustion chamber, and supplying a second flow of fuel and a second flow of compressed air to the at least one fuel cup.

公开(公告)号：US20240318821A1

公开(公告)日：2024-09-26

申请号：US18186518

申请日：2023-03-20

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Manampathy G. Giridharan ,  Pradeep Naik ,  Michael A. Benjamin

IPC: F23R3/06

CPC classification number: F23R3/06 ,  F23R3/26

Abstract: A combustor having a casing, an inner liner, an outer liner, a compressed air passageway, a combustion chamber and at least one dilution passage. The compressed air passageway being formed between the casing, the inner liner and the outer liner. The combustion chamber being at least partially defined by the inner liner and the outer liner. The at least one dilution passage extending through at least one of the inner liner or the outer liner. The at least one dilution passage extending between an inlet fluidly coupled to the compressed air passageway and a dilution hole fluidly coupled to the combustion chamber.

公开(公告)号：US20240318598A1

公开(公告)日：2024-09-26

申请号：US18736683

申请日：2024-06-07

Applicant: General Electric Company

Inventor： Michael A. Benjamin ,  Manampathy G. Giridharan

IPC: F02C7/22 ,  F23R3/28

CPC classification number: F02C7/22 ,  F23R3/28

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：US12092332B2

公开(公告)日：2024-09-17

申请号：US17675270

申请日：2022-02-18

Applicant: General Electric Company

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

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

CPC classification number: F23R3/286 ,  F02C7/22 ,  F23C7/004 ,  F23D17/002 ,  F23L7/002 ,  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：US12038176B2

公开(公告)日：2024-07-16

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: F23R3/14 ,  F23R3/28 ,  F23D11/38

CPC classification number: F23R3/14 ,  F23R3/286 ,  F23D11/383

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：US12037128B2

公开(公告)日：2024-07-16

申请号：US17209719

申请日：2021-03-23

Applicant: General Electric Company

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

IPC: B64D37/32 ,  B64D27/10 ,  B64D37/04 ,  B64D37/30 ,  B64D37/34 ,  C06B23/00 ,  C06B43/00

CPC classification number: B64D37/32 ,  B64D27/10 ,  B64D37/04 ,  B64D37/30 ,  B64D37/34 ,  C06B23/008 ,  C06B43/00

Abstract: A hydrogen fuel including a safety marker and a method and apparatus for adding the safety marker to the hydrogen fuel. The hydrogen fuel may be stored in a tank in a liquid phase and then heated to at least one of a gaseous phase and a supercritical phase. The safety marker may be added to the hydrogen fuel when the hydrogen fuel is in the at least one of the gaseous phase and the supercritical phase after heating the hydrogen fuel. The hydrogen fuel may be delivered in the at least one of the gaseous phase and the supercritical phase to a power generator, such as a gas turbine engine. The safety marker may be a visual safety marker, such as a noble gas, or an odorant.

公开(公告)号：US12012903B2

公开(公告)日：2024-06-18

申请号：US17719659

申请日：2022-04-13

Applicant: General Electric Company

Inventor： Hejie Li ,  Michael A. Benjamin ,  Nicholas Ryan Overman

IPC: F02C9/28 ,  F02C7/224

CPC classification number: F02C9/28 ,  F02C7/224 ,  F05D2220/323 ,  F05D2240/35 ,  F05D2270/20 ,  F05D2270/301 ,  F05D2270/303

Abstract: A fuel temperature control system and a method of controlling a fuel temperature for a turbine engine including supplying an aviation fuel to a fuel nozzle fluidly coupled to a combustion chamber. A fuel temperature sensor for determining at least one input parameter to define an inlet fuel temperature of the aviation fuel in the fuel nozzle. A controller for receiving the at least one input parameter and for calculating a calculated flow number in the fuel nozzle. The controller capable of comparing the calculated flow number and a reference flow number associated with a threshold during a steady state condition to determine if the aviation fuel is boiling inside the fuel nozzle.

公开(公告)号：US11906165B2

公开(公告)日：2024-02-20

申请号：US17717739

申请日：2022-04-11

Applicant: General Electric Company

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

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. The fuel nozzle can include both a primary and secondary fuel passage, and an additional air passage to provide for greater flame control, fuel provision, or local fuel and air mixing prior to combustion.