公开(公告)号：US20180252410A1

公开(公告)日：2018-09-06

申请号：US15447847

申请日：2017-03-02

Applicant: General Electric Company

Inventor： Joseph Zelina ,  Sarah Marie Monahan ,  Michael Anthony Benjamin ,  Venkat Eswarlu Tangirala ,  Sibtosh Pal ,  William Thomas Ross

IPC: F23R3/06 ,  F23R3/00 ,  F23R3/42

Abstract: A combustor for a turbine engine includes an inner combustion liner and an outer combustion liner together defining at least in part an interior. The interior includes a combustion chamber and a main portion. The combustor also includes an inlet combustion liner at least partially defining the combustion chamber of the interior and including an inlet assembly. The inlet assembly includes at least two cavity air tubes arranged along the axial direction, each cavity air tube extending between an inlet and an outlet, the outlet of each cavity air tube in airflow communication with the combustion chamber for providing the combustion chamber with a flow of air.

公开(公告)号：US12055297B2

公开(公告)日：2024-08-06

申请号：US17358377

申请日：2021-06-25

Applicant: General Electric Company

Inventor： Gregory Allen Boardman ,  Michael Anthony Benjamin ,  Clayton Stuart Cooper ,  Joseph Zelina ,  Eric John Stevens

IPC: F23R3/34 ,  F23R3/18 ,  F23R3/52 ,  F23R3/58 ,  F23C9/00 ,  F23R3/12

CPC classification number: F23R3/34 ,  F23R3/18 ,  F23R3/52 ,  F23R3/58 ,  F23C9/006 ,  F23R3/12 ,  F23R3/346 ,  F23R2900/00015

Abstract: Various embodiments include a trapped vortex combustor and a method for operating trapped vortex combustor. In one embodiment, the trapped vortex combustor comprises a trapped vortex combustion zone and at least one secondary combustion zone disposed downstream of the trapped vortex combustion zone. The trapped vortex combustion zone is operable to receive and combust a first fuel and a first air and produce a first combustion product flowing toroidally therein. The at least one secondary combustion zone is operable to receive and combust the first combustion product and at least one second injection consisting of fuel and/or air and produce at least one second combustion product therein. The combustor may reduce the residence time of the highest temperature combustion products and achieve the lower NOx emission.

公开(公告)号：US11959441B2

公开(公告)日：2024-04-16

申请号：US18049028

申请日：2022-10-24

Applicant: General Electric Company

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

IPC: F02K7/10 ,  F02K7/08 ,  F02K7/20 ,  F23R3/18 ,  F23R3/34 ,  F23R7/00

CPC classification number: F02K7/10 ,  F02K7/08 ,  F02K7/20 ,  F23R3/18 ,  F23R3/34 ,  F23R7/00 ,  F05D2220/10

Abstract: A Brayton cycle engine including a longitudinal wall extended along a lengthwise direction. The longitudinal wall defines a gas flowpath of the engine. An inner wall assembly is extended from the longitudinal wall into the gas flowpath. The inner wall assembly defines a detonation combustion region in the gas flowpath upstream of the inner wall assembly.

公开(公告)号：US20230243505A1

公开(公告)日：2023-08-03

申请号：US17588876

申请日：2022-01-31

Applicant: GENERAL ELECTRIC COMPANY

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

IPC: F02C9/40 ,  F02C7/22 ,  F23R3/28

CPC classification number: F02C9/40 ,  F02C7/22 ,  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：US20230213192A1

公开(公告)日：2023-07-06

申请号：US18049018

申请日：2022-10-24

Applicant: General Electric Company

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

IPC: F23R3/18 ,  F02K7/10 ,  F02K7/20 ,  F23R7/00 ,  F23R3/34 ,  F02K7/08

CPC classification number: F23R3/18 ,  F02K7/10 ,  F02K7/20 ,  F23R7/00 ,  F23R3/34 ,  F02K7/08 ,  F05D2220/10

Abstract: A Brayton cycle engine including a longitudinal wall extended along a lengthwise direction. The longitudinal wall defines a gas flowpath of the engine. An inner wall assembly is extended from the longitudinal wall into the gas flowpath. The inner wall assembly defines a detonation combustion region in the gas flowpath upstream of the inner wall assembly.

公开(公告)号：US11578871B1

公开(公告)日：2023-02-14

申请号：US17587634

申请日：2022-01-28

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Narendra D. Joshi ,  Joseph Zelina

IPC: 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 primary fuel injector fluidly coupled to the dome inlet, and a second fuel injector fluidly coupled to the combustion chamber.

公开(公告)号：US11320147B2

公开(公告)日：2022-05-03

申请号：US15904918

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 ,  F23R7/00 ,  F02K7/10 ,  F02K7/08 ,  F23R3/34

Abstract: A Brayton cycle engine including an inner wall assembly defining a detonation combustion region upstream thereof extended from a longitudinal wall into a gas flowpath. An actuator adjusts a depth of the detonation combustion region into the gas flowpath. A method for operating the engine includes flowing an oxidizer through the gas flowpath; capturing a portion of the flow of oxidizer via the inner wall; flowing a first flow of fuel to the captured flow of oxidizer; producing a rotating detonation gases via a mixture of the first flow of fuel and the captured flow of oxidizer; flowing at least a portion of the detonation gases downstream to mix with the flow of oxidizer; flowing a second flow of fuel to the mixture of detonation gases and oxidizer; and burning the mixture of the second flow of fuel and the detonation gases/oxidizer mixture.

公开(公告)号：US11131461B2

公开(公告)日：2021-09-28

申请号：US16700072

申请日：2019-12-02

Applicant: General Electric Company

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

IPC: F23R3/36 ,  F23R7/00 ,  F23R3/56 ,  F02C5/00 ,  F02K7/02

Abstract: A method and system of effervescent atomization of liquid fuel for a rotating detonation combustor (RDC) for a propulsion system is provided. The method includes flowing liquid fuel through a fuel injection port of a nozzle assembly of the RDC system; flowing a gas through the fuel injection port of the nozzle assembly volumetrically proportional to the liquid fuel; producing a gas-liquid fuel mixture at the fuel injection port by mixing the flow of gas and the flow of liquid fuel; flowing an oxidizer through a nozzle flowpath of the RDC system; producing an oxidizer-gas-liquid fuel mixture by mixing the gas-liquid fuel mixture and the flow of oxidizer within the nozzle flowpath; and igniting the oxidizer-gas-liquid fuel mixture within a combustion chamber of the RDC system.

公开(公告)号：US10823422B2

公开(公告)日：2020-11-03

申请号：US15785726

申请日：2017-10-17

Applicant: General Electric Company

Inventor： Arthur Wesley Johnson ,  Joseph Zelina ,  Eric John Stevens ,  Clayton Stuart Cooper ,  Beverly Stephenson Duncan ,  Juntao Zhang

IPC: F23R3/58 ,  F23R3/14 ,  F23R3/12 ,  F23R3/18 ,  F23R3/04 ,  F23R3/50 ,  F01D25/00

Abstract: A trapped vortex combustor for use in a gas turbine engine defines a radial direction, an axial direction, and a circumferential direction. The trapped vortex combustor includes an outer vortex chamber wall defining a forward end, and a dome attached to, or formed integrally with, the outer vortex chamber wall at the forward end of the outer vortex chamber wall. The dome and outer vortex chamber wall define at least in part a combustion chamber having an outer trapped vortex chamber. The dome includes an air chute defining an airflow direction. The radial direction and axial direction of the trapped vortex combustor define a reference plane extending through the air chute, the airflow direction of the air chute defining an angle greater than zero with the reference plane.

公开(公告)号：US20200088101A1

公开(公告)日：2020-03-19

申请号：US16675787

申请日：2019-11-06

Applicant: General Electric Company

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

IPC: F02C7/18 ,  F02C3/14 ,  F23R3/00 ,  F02C7/10 ,  F01D1/24 ,  F01D9/02

Abstract: The present disclosure is directed to a propulsion system including a wall defining a combustion chamber inlet, a combustion chamber outlet, and a combustion chamber therebetween, a nozzle assembly disposed at the combustion chamber inlet, the nozzle assembly configured to provide a fuel/oxidizer mixture to the combustion chamber, a turbine nozzle coupled to the wall and positioned at the combustion chamber outlet, wherein the turbine nozzle defines a cooling circuit within the turbine nozzle, and a casing positioned radially adjacent to the wall, wherein a channel structure is positioned between the casing and the wall, the channel structure in fluid communication with the cooling circuit within the turbine nozzle, and wherein a flowpath is formed between the wall and the casing, the flowpath in fluid communication from the cooling circuit at the turbine nozzle to the nozzle assembly to provide a flow of oxidizer to the thereto.