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.

公开(公告)号：US20190264917A1

公开(公告)日：2019-08-29

申请号：US15904868

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. 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：US20190120493A1

公开(公告)日：2019-04-25

申请号：US15793129

申请日：2017-10-25

Applicant: General Electric Company

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

IPC: F23R3/58 ,  F02C3/14 ,  F23R3/34 ,  F23R3/28 ,  F02K3/077

Abstract: A combustor assembly is generally provided. The combustor assembly includes a volute wall extended annularly around a combustor centerline, an annular inner wall extended at least partially along a lengthwise direction from the volute wall, and an annular outer wall extended at least partially along the lengthwise direction from the volute wall. The volute wall is extended at least partially as a spiral curve from a circumferential reference line around the combustor centerline and defines a combustion chamber within the volute wall. The inner wall and the outer wall are 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. A flow passage wall is extended to a portion of the volute wall and a portion of the outer wall. The flow passage wall defines a secondary flow passage and a tertiary flow passage between the volute wall, the outer wall, and the flow passage wall. The secondary flow passage and the tertiary flow passage are each in adjacent circumferential arrangement of one another around the combustor centerline. The volute wall and the outer wall together define one or more secondary outlet openings adjacent to the combustion chamber and in fluid communication with the combustion chamber. The outer wall defines one or more tertiary outlet openings in fluid communication with the tertiary flow passage and the primary flow passage.

公开(公告)号：US20190086092A1

公开(公告)日：2019-03-21

申请号：US15709958

申请日：2017-09-20

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

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：US20180355822A1

公开(公告)日：2018-12-13

申请号：US15618289

申请日：2017-06-09

Applicant: General Electric Company

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

IPC: F02K7/00

CPC classification number: F02K7/005

Abstract: The present disclosure is directed to a rotating detonation combustion system for a propulsion system including a plurality of combustors in adjacent arrangement along the circumferential direction. Each combustor defines a combustor centerline extended through each combustor, and each combustor comprises an outer wall defining a combustion chamber and a combustion inlet. Each combustion chamber is defined by an annular gap and a combustion chamber length together defining a volume of each combustion chamber. Each combustor defines a plurality of nozzle assemblies each disposed at the combustion inlet in adjacent arrangement around each combustor centerline. Each nozzle assembly defines a nozzle wall extended along a lengthwise direction, a nozzle inlet, a nozzle outlet, and a throat therebetween, and each nozzle assembly defines a converging-diverging nozzle. A first array of combustors defines a first volume and a second array of combustors defines a second volume different from the first volume.

公开(公告)号：US12173898B1

公开(公告)日：2024-12-24

申请号：US18486368

申请日：2023-10-13

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：US20240230100A9

公开(公告)日：2024-07-11

申请号：US18314565

申请日：2023-05-09

Applicant: General Electric Company

Inventor： Ravindra Shankar Ganiger ,  Hiranya Nath ,  Michael A. Benjamin ,  Daniel D. Brown ,  Sibtosh Pal ,  Joseph Zelina

IPC: F23R3/60 ,  F02C7/20 ,  F23R3/06

CPC classification number: F23R3/60 ,  F02C7/20 ,  F23R3/06 ,  F23R2900/00017 ,  F23R2900/03042

Abstract: A coupling assembly for a turbine engine. The coupling assembly includes a cold side component, a hot side component, and a fastening mechanism. The cold side component and the hot side component together at least partially form a combustion chamber. The fastening mechanism couples the hot side component to the cold side component. The fastening mechanism includes a stud disposed through the cold side component and a cap positioned on the stud. The cap defines a hollow interior and includes one or more first cap cooling holes. The one or more first cap cooling holes operably direct cooling air into the hollow interior such that the hollow interior provides a cushion of air between the combustion chamber and the stud.

公开(公告)号：US11970993B2

公开(公告)日：2024-04-30

申请号：US17935646

申请日：2022-09-27

Applicant: General Electric Company

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

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

CPC classification number: F02K7/10 ,  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：US11774103B2

公开(公告)日：2023-10-03

申请号：US17658750

申请日：2022-04-11

Applicant: General Electric Company

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

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

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