公开(公告)号：US20250075910A1

公开(公告)日：2025-03-06

申请号：US18952330

申请日：2024-11-19

Applicant: GENERAL ELECTRIC COMPANY

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

IPC: F23R3/00 ,  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. A combustion section for the turbine engine, having a primary combustor liner including an inner liner and an outer liner annular about an engine centerline. A dome wall extending between the inner liner and the outer liner. A set of primary dome inlets located in the dome wall and circumferentially arranged about the engine centerline. A set of secondary combustors fluidly coupled to a primary combustion chamber, the set of secondary combustors including a first mini combustor and a second mini combustor.

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：US12169068B2

公开(公告)日：2024-12-17

申请号：US17819399

申请日：2022-08-12

Applicant: General Electric Company

Inventor： Joseph Zelina ,  Shai Birmaher ,  Sibtosh Pal ,  Clayton S. Cooper

IPC: F23R3/00 ,  F23R3/28

Abstract: A combustor for a turbine engine. The combustor includes a fuel injector and a fluid injection system in fluid communication with the combustor. The fuel injector includes a mixer assembly with a pilot mixer and a main mixer. The pilot mixer and the main mixer operate during high power operation of the turbine engine. The fluid injection system injects a fluid into the combustor during high power operation of the turbine engine. The fluid is shut off during low power operation of the turbine engine and during mid-level power operation of the turbine engine.

公开(公告)号：US20240287952A1

公开(公告)日：2024-08-29

申请号：US18643376

申请日：2024-04-23

Applicant: General Electric Company

Inventor： Sibtosh Pal ,  Steven Clayton Vise ,  Arthur Wesley Johnson ,  Clayton Stuart Cooper ,  Joseph Zelina

IPC: F02K7/10 ,  F02K7/02 ,  F02K7/08 ,  F02K7/16 ,  F23R3/18 ,  F23R3/34 ,  F23R7/00

CPC classification number: F02K7/10 ,  F02K7/02 ,  F02K7/08 ,  F02K7/16 ,  F23R7/00 ,  F05D2220/10 ,  F05D2250/90 ,  F23R3/18 ,  F23R3/34

Abstract: A Brayton cycle engine and method for operation. The engine includes an inner wall assembly and an upstream wall assembly each extended from a longitudinal wall into a gas flowpath. An actuator adjusts a depth of the detonation combustion region into the gas flowpath between the inner wall assembly and the upstream wall assembly. The engine flows an oxidizer through the gas flowpath and the inner wall captures a portion of the oxidizer. The engine further adjusts the captured flow of oxidizer via the upstream wall and flows a first flow of fuel to the captured flow of oxidizer to produce rotating detonation gases. The engine flows the detonation gases downstream and to mix with the flow of oxidizer, and flows and burns a second flow of fuel to the detonation gases/oxidizer mixture to produce thrust.

公开(公告)号：US11906168B2

公开(公告)日：2024-02-20

申请号：US17198150

申请日：2021-03-10

Applicant: General Electric Company

Inventor： Gregory Allen Boardman ,  Pradeep Naik ,  Joseph Zelina ,  Clayton Stuart Cooper

IPC: F23R3/42 ,  F23R3/28 ,  F23R3/58 ,  F02C3/14 ,  F23R3/34 ,  F02C7/22 ,  F23R3/12

CPC classification number: F23R3/286 ,  F02C3/14 ,  F23R3/346 ,  F23R3/42 ,  F23R3/58 ,  F02C7/22 ,  F23R3/12 ,  F23R3/34 ,  F23R2900/00015

Abstract: A combustor assembly is generally provided. The combustor assembly includes a volute wall extended annularly around a combustor centerline. The volute wall is extended at least partially as a spiral curve from a circumferential reference line around the combustor centerline. The volute wall defines a combustion chamber therewithin. An annular inner wall is extended at least partially along a lengthwise direction from the volute wall. An annular outer wall is extended at least partially along the lengthwise direction from the volute wall. The inner wall and the outer wall are each separated along a radial direction from the combustor centerline. A primary flow passage is defined between the inner wall and the outer wall in fluid communication from the combustion chamber.

公开(公告)号：US20240053013A1

公开(公告)日：2024-02-15

申请号：US17819399

申请日：2022-08-12

Applicant: General Electric Company

Inventor： Joseph Zelina ,  Shai Birmaher ,  Sibtosh Pal ,  Clayton S. Cooper

IPC: F23R3/28

CPC classification number: F23R3/286

Abstract: A combustor for a turbine engine. The combustor includes a fuel injector and a fluid injection system in fluid communication with the combustor. The fuel injector includes a mixer assembly with a pilot mixer and a main mixer. The pilot mixer and the main mixer operate during high power operation of the turbine engine. The fluid injection system injects a fluid into the combustor during high power operation of the turbine engine. The fluid is shut off during low power operation of the turbine engine and during mid-level power operation of the turbine engine.

公开(公告)号：US11885498B2

公开(公告)日：2024-01-30

申请号：US17588876

申请日：2022-01-31

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Narendra D. Joshi ,  Lawrence B. Kool ,  Joseph Zelina

IPC: F23R3/34 ,  F23R3/40 ,  F02C9/40 ,  F23R3/36 ,  F02C7/22 ,  F23R3/28

CPC classification number: F23R3/40 ,  F02C7/22 ,  F02C9/40 ,  F23R3/34 ,  F23R3/36 ,  F23R3/28

Abstract: A gas turbine engine with a compressor section, a turbine section, and a combustion section located downstream from the compressor section and upstream from the turbine section, the combustion section including a dome inlet, a combustor outlet fluidly coupled to the turbine section, a liner and a dome assembly together at least partially defining a combustion chamber extending between the dome inlet and the combustor outlet, a fuel system fluidly coupled to the combustion section, the fuel system comprising a fuel supply, a primary fuel line fluidly coupling the fuel supply to the combustion section, and a reformer fluidly coupled to the fuel supply.

公开(公告)号：US11073114B2

公开(公告)日：2021-07-27

申请号：US16217546

申请日：2018-12-12

Applicant: General Electric Company

Inventor： Gregory Allen Boardman ,  Pradeep Naik ,  Clayton Stuart Cooper ,  Joseph Zelina

IPC: F02M29/06 ,  F02M61/14 ,  F23R3/14 ,  F23R3/28

Abstract: Embodiments of a combustion section including a fuel injector assembly are provided. The combustion section includes the fuel injector assembly coupled to an outer casing and a liner assembly. The fuel injector assembly includes a body defining a first inlet opening and a second inlet opening spaced apart from one another along a first direction. The body further defines a fuel-oxidizer mixing passage therewithin extended along a second direction at least partially orthogonal to the first direction. The first inlet opening and the second inlet opening are each in fluid communication with the fuel-oxidizer mixing passage. The body defines an outlet opening at the fuel-oxidizer mixing passage at a distal end relative to the first inlet opening and the second inlet opening. The first inlet opening and the second inlet opening are each configured to admit a flow of oxidizer to the fuel-oxidizer mixing passage. The fuel-oxidizer mixing passage is configured to provide a flow of fuel-oxidizer mixture to a combustion chamber via the outlet opening.

公开(公告)号：US20190264918A1

公开(公告)日：2019-08-29

申请号：US15904892

申请日：2018-02-26

Applicant: General Electric Company

Inventor： Sibtosh Pal ,  Steven Clayton Vise ,  Arthur Wesley Johnson ,  Clayton Stuart Cooper ,  Joseph Zelina

IPC: F23R3/18 ,  F23R3/34 ,  F23R3/56 ,  F02K7/10 ,  F02K7/08

Abstract: A Brayton cycle engine including a longitudinal wall extended along a lengthwise direction. The longitudinal wall defines a gas flowpath of the engine. A strut is extended through the gas flowpath between the longitudinal walls. An inner wall assembly is extended from the longitudinal wall and the strut into the gas flowpath. The inner wall assembly and strut together define a plurality of detonation combustion regions in the gas flowpath upstream of the inner wall assembly.

公开(公告)号：US20190242582A1

公开(公告)日：2019-08-08

申请号：US15890637

申请日：2018-02-07

Applicant: General Electric Company

Inventor： Arthur Wesley Johnson ,  Steven Clayton Vise ,  Clayton Stuart Cooper ,  Joseph Zelina ,  Sibtosh Pal

IPC: F23R3/56 ,  F02C3/04 ,  F23R3/28

CPC classification number: F23R3/56 ,  F02C3/04 ,  F05D2220/32 ,  F05D2240/35 ,  F23R3/04 ,  F23R3/286 ,  F23R2900/03042

Abstract: A rotating detonation combustion (RDC) system including a detonation chamber wall extended along a longitudinal direction. The detonation chamber wall defines a detonation chamber radially in between the detonation chamber walls. The RDC system further includes a fuel-oxidizer nozzle defining a first convergent-divergent nozzle disposed upstream of the detonation chamber, and a gas nozzle defining a second convergent-divergent nozzle extended through the detonation chamber wall at least partially along the longitudinal direction. The gas nozzle provides a flow of gas into the detonation chamber at least partially co-directional to the detonation chamber wall.