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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
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.
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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
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.
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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
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.
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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
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.
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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
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.
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Patent Agency Ranking
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
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.
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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
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.
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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
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.
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39.发明授权公开(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
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.
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公开(公告)号：US11788724B1
公开(公告)日：2023-10-17
申请号：US17929360
申请日：2022-09-02
Applicant: General Electric Company
Inventor： Hiranya Nath , Ravindra Shankar Ganiger , Michael A. Benjamin
CPC classification number: F23R3/002 , F02C7/045 , F23R3/04 , F05D2240/35 , F05D2260/96 , F23R2900/00014
Abstract: A combustor liner has an outer liner and an inner liner that define a combustion chamber therebetween, the combustion chamber having a dilution zone. The outer liner and the inner liner each have a converging-diverging section extending into the dilution zone of the combustion chamber and form a throat between them. A bridge member extends across the converging-diverging sections to form a damper cavity therebetween. Each of the converging-diverging sections includes at least one dilution opening defined through the respective converging-diverging section at the throat, and includes a damper inlet feed member on a downstream portion of the converging-diverging section, so that an acoustic damper is defined by the converting-diverging section, the bridge, and the damper inlet feed. The acoustic damper dampens acoustic characteristics of the combustor.
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