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：US11181274B2

公开(公告)日：2021-11-23

申请号：US15681875

申请日：2017-08-21

Applicant: General Electric Company

Inventor： Allen Michael Danis ,  Scott Matthew Bush ,  Arthur Wesley Johnson ,  Nicholas Ryan Overman ,  Kent Hamilton Lyle ,  Eric John Stevens

IPC: F23R3/36 ,  F02C9/40 ,  F23R3/28 ,  F02C7/22 ,  F02C3/20 ,  F02C3/06 ,  F02C7/228 ,  F23R3/34 ,  F02C9/28

Abstract: The present disclosure is directed to a method of operating a combustion system to attenuate combustion dynamics. The method includes flowing, via a compressor section, an overall supply of air to the combustion system; flowing, via a fuel supply system, an overall flow of fuel to the combustion system; flowing, to a first fuel nozzle of the combustion system, a first supply of fuel defining a richer burning fuel-air mixture at the first fuel nozzle; flowing, to a second fuel nozzle of the combustion system, a second supply of fuel defining a leaner burning fuel-air mixture at the second fuel nozzle; and igniting the richer burning fuel-air mixture and the leaner burning fuel-air mixture to produce an overall fuel-air ratio at a combustion chamber of the combustion system.

公开(公告)号：US20200041129A1

公开(公告)日：2020-02-06

申请号：US16055494

申请日：2018-08-06

Applicant: General Electric Company

Inventor： Sibtosh Pal ,  Clayton Stuart Cooper ,  Arthur Wesley Johnson ,  Steven Clayton Vise ,  Michael Anthony Benjamin ,  Allen Michael Danis

IPC: F23R3/28 ,  F23C7/00 ,  F23R3/14

Abstract: A mixer assembly for a turbine engine is generally provided. The mixer assembly includes a vane assembly including a plurality of vanes configured to direct a flow of oxidizer to mix with a flow of fuel. The vane assembly includes a fluid diode disposed within a vane flow path between each pair of vanes of the vane assembly.

公开(公告)号：US20200041127A1

公开(公告)日：2020-02-06

申请号：US16051838

申请日：2018-08-01

Applicant: General Electric Company

Inventor： Perumallu Vukanti ,  Hiranya Kumar Nath ,  Jayanth Sekar ,  Arthur Wesley Johnson ,  Gurunath Gandikota ,  Mayank Krisna Amble ,  Clayton Stuart Cooper

IPC: F23R3/18 ,  F23R3/00

Abstract: The present disclosure is directed to a combustor assembly for a gas turbine engine. The combustor assembly includes a liner defining a combustion chamber therewithin and a pressure plenum surrounding the liner. The liner defines an opening. The liner includes a walled chute disposed at least partially within the opening. The walled chute defines an inner surface at least partially defining a jet destabilizer.

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.

公开(公告)号：US20190085767A1

公开(公告)日：2019-03-21

申请号：US15705314

申请日：2017-09-15

Applicant: General Electric Company

Inventor： Steven Clayton Vise ,  Allen Michael Danis ,  Jayanth Sekar ,  Pradeep Naik ,  Perumallu Vukanti ,  Arthur Wesley Johnson ,  Clayton Stuart Cooper ,  Karthikeyan Sampath

IPC: F02C3/22 ,  F23R3/00 ,  F23R3/04

Abstract: An apparatus and method for a combustor, the combustor including combustor liner having a plurality of dilution openings. The combustor receives a flow of fuel that is ignited and mixed with dilution air to form a flow of combustion gases. The flow of combustion gases travels through the combustor to a turbine section of an engine.

公开(公告)号：US11473780B2

公开(公告)日：2022-10-18

申请号：US15904991

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: F23R7/00 ,  F02K7/08 ,  F02K7/10 ,  F02K7/16 ,  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：US11359578B2

公开(公告)日：2022-06-14

申请号：US16055313

申请日：2018-08-06

Applicant: General Electric Company

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

IPC: F02K7/10 ,  F02K7/08 ,  F02C7/042 ,  F02K1/08

Abstract: A ramjet engine and system and method for operation is generally provided. The ramjet includes a longitudinal wall extended along a lengthwise direction. The longitudinal wall defines an inlet section, a combustion section, and an exhaust section. A fuel nozzle assembly is extended from the longitudinal wall. The fuel nozzle assembly defines a nozzle throat area. The fuel nozzle assembly is moveable along a radial direction to adjust the nozzle throat area based at least on a difference in pressure of a flow of fluid at an inlet of the inlet section and a pressure of the flow of fluid at the fuel nozzle assembly.

公开(公告)号：US20190264920A1

公开(公告)日：2019-08-29

申请号：US15904991

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 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.