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：US11286884B2

公开(公告)日：2022-03-29

申请号：US16217625

申请日：2018-12-12

Applicant: General Electric Company

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

IPC: F23R3/34 ,  F02C9/26 ,  F23R3/28 ,  F02K3/10 ,  F23R3/10 ,  F02C3/04

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：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：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：US20190024895A1

公开(公告)日：2019-01-24

申请号：US15652378

申请日：2017-07-18

Applicant: General Electric Company

Inventor： Richard Wade Stickles ,  Clayton Stuart Cooper ,  Perumallu Vukanti ,  Mayank Krisna Amble

IPC: F23R3/06 ,  F23R3/00

Abstract: The present disclosure is directed to a combustor assembly for a gas turbine engine. The combustor assembly includes an inner liner and an outer liner together defining a combustion chamber therebetween and a pressure plenum surrounding the inner liner and the outer liner. One or more of the inner liner and the outer liner defines one or more openings. The one or more liners includes a walled chute disposed at least partially within the opening. A structural member extends from the one or more liners to the walled chute.