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.

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：US20250155124A1

公开(公告)日：2025-05-15

申请号：US18507877

申请日：2023-11-13

Applicant: General Electric Company

Inventor： Joseph Zelina ,  Clayton S. Cooper ,  Sibtosh Pal ,  Pradeep Naik ,  Sripathi Mohan ,  Michael A. Benjamin

IPC: F23R3/34 ,  F02C3/30

Abstract: A turbine engine includes a compressor section for providing a compressed air flow, a fuel system for providing a primary combustor fuel supply, and a secondary combustor fuel supply. A primary combustor, located downstream of the compressor section, combusts the compressed air flow and the primary combustor fuel supply to generate primary combustion products. A turbine section, located downstream of the primary combustor, includes a turbine and a secondary combustor that further combusts the primary combustion products and the fuel from the secondary combustor fuel supply. A steam system provides a steam supply to the secondary combustor. The secondary combustor further combusts the primary combustion products and the secondary combustor fuel supply to generate secondary combustion products, and the turbine section is rotated by the secondary combustor steam supply and the inter-turbine combustion products.

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.