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公开(公告)号：US11143106B2
公开(公告)日：2021-10-12
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: F23R7/00 , F02C7/18 , F01D9/02 , F02C3/14 , F23R3/00 , F02C7/10 , F01D1/24 , F23R3/28 , F01D25/12 , F23R3/50
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.
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公开(公告)号：US10724739B2
公开(公告)日：2020-07-28
申请号：US15468172
申请日：2017-03-24
Applicant: General Electric Company
Inventor： Kwanwoo Kim , Owen Graham , Clayton Stuart Cooper
Abstract: The present disclosure is directed to a combustor assembly for a gas turbine engine. The combustor assembly includes an annular bulkhead adjacent to a diffuser cavity; a deflector downstream of the bulkhead and adjacent to a combustion chamber; a bulkhead support coupled to an upstream side of the deflector; a first walled enclosure coupled to the bulkhead support; and a second walled enclosure coupled to the first walled enclosure. The deflector and the bulkhead support together define a bulkhead conduit therethrough to the combustion chamber. The first walled enclosure defines a first cavity and a hot side orifice. The hot side orifice is adjacent to and in fluid communication with the bulkhead conduit. The second walled enclosure defines a second cavity and a second opening adjacent to a diffuser cavity.
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公开(公告)号：US20190271268A1
公开(公告)日：2019-09-05
申请号：US15909196
申请日：2018-03-01
Applicant: General Electric Company
Inventor： Arthur Wesley Johnson , Steven Clayton Vise , Clayton Stuart Cooper , Joseph Zelina , Sibtosh Pal
Abstract: A turbine engine including a compressor rotor and a rotating detonation combustion (RDC) system. The compressor rotor includes a compressor airfoil defining a trailing edge disposed within a core flowpath of the turbine engine. The core flowpath defines a radial distance between an outer radius and an inner radius at the compressor rotor. The RDC system includes an outer wall and an inner wall each extended along a lengthwise direction and defining a detonation chamber therebetween. The RDC system further includes a strut defining a nozzle assembly and a fuel injection opening providing a flow of fuel to the detonation chamber. The compressor rotor provides a flow of oxidizer in direct fluid communication to the nozzle assembly of the RDC system.
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公开(公告)号：US20180363555A1
公开(公告)日：2018-12-20
申请号：US15623773
申请日：2017-06-15
Applicant: General Electric Company
Inventor： Joseph Zelina , Sibtosh Pal , Arthur Wesley Johnson , Clayton Stuart Cooper , Steven Clayton Vise
Abstract: The present disclosure is directed to a propulsion system including an annular inner wall and an annular outer wall, a nozzle assembly, a turbine nozzle, and an inner casing and an outer casing. The inner wall and outer wall together extend at least partially along a longitudinal direction and together define a combustion chamber inlet, a combustion chamber outlet, and a combustion chamber therebetween. The nozzle assembly is disposed at the combustion inlet and provides a mixture of fuel and oxidizer to the combustion chamber. The turbine nozzle defines a plurality of airfoils in adjacent circumferential arrangement disposed at the combustion chamber outlet. The turbine nozzle is coupled to the outer wall and the inner wall. The inner casing is disposed inward of the inner wall and the outer casing is disposed outward of the outer wall. Each of the inner casing and the outer casing are coupled to the turbine nozzle. A primary flowpath is defined between the inner casing and the inner wall, through the turbine nozzle, and between the outer casing and the outer wall, and in fluid communication with the combustion chamber.
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公开(公告)号：US20180356094A1
公开(公告)日：2018-12-13
申请号：US15618431
申请日：2017-06-09
Applicant: General Electric Company
Inventor： Joseph Zelina , Sibtosh Pal , Arthur Wesley Johnson , Clayton Stuart Cooper , Steven Clayton Vise
Abstract: The present disclosure is directed to a method of operating a propulsion system at an approximately constant detonation cell quantity in the combustion chamber of a detonation combustion system. The propulsion system defines an inlet section upstream of the rotating detonation combustion system and an exhaust section downstream of the rotating detonation combustion system. The method includes providing an outer wall and an inner wall together defining an annular gap and a combustion chamber length extended from a combustion chamber inlet proximate to the fuel-oxidizer mixing nozzle to a combustion chamber exit proximate to the exhaust section of the propulsion system, the annular gap and the combustion chamber length together defining a first volume at a first operating condition defining a lowest steady state pressure and temperature at the rotating detonation combustion system; providing a mixture of a fuel and an oxidizer to the combustion chamber via the fuel-oxidizer mixing nozzle; detonating the fuel and oxidizer mixture in the combustion chamber, wherein the detonation produces a detonation cell size; and adjusting the volume of the combustion chamber via articulating one or more of the outer wall, the inner wall, and the fuel-oxidizer mixing nozzle such that one or more of the annular gap and the combustion chamber length is changed based on one or more operating conditions.
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Patent Agency Ranking
36.发明申请公开(公告)号：US20180356093A1
公开(公告)日：2018-12-13
申请号：US15618380
申请日：2017-06-09
Applicant: General Electric Company
Inventor： Sibtosh Pal , Joseph Zelina , Arthur Wesley Johnson , Clayton Stuart Cooper , Steven Clayton Vise
CPC classification number: F23R3/04 , F02C5/12 , F05D2220/32 , F05D2240/35
Abstract: The present disclosure is directed to a method of operating a propulsion system including a rotating detonation combustion (RDC) system. The RDC system defines a combustion inlet at an upstream end, a combustion outlet at a downstream end, a combustion chamber therebetween, and a nozzle defined at the combustion inlet upstream of the combustion chamber, and a secondary flowpath extended from upstream of the nozzle to downstream of the nozzle. The method includes providing the combustion chamber of the rotating detonation combustion system to produce a detonation cell size configured for a first operating condition defining a lowest steady state operating condition of the propulsion system; generating a flow of oxidizer to the combustion inlet of the combustion section; providing a first portion of the flow of oxidizer to the combustion chamber and mixing the first portion of the flow of oxidizer with a fuel; providing a second portion of the flow of oxidizer to the secondary flowpath, wherein the secondary flowpath bypasses the combustion chamber; and adjusting a ratio of the first portion of the flow of oxidizer through the combustion chamber versus the second portion of the flow of oxidizer through the secondary flowpath based at least on a commanded power output of the propulsion system.
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公开(公告)号：US20180355792A1
公开(公告)日：2018-12-13
申请号：US15618495
申请日：2017-06-09
Applicant: General Electric Company
Inventor： Sibtosh Pal , Joseph Zelina , Arthur Wesley Johnson , Clayton Stuart Cooper , Steven Clayton Vise
Abstract: The present disclosure is directed to a rotating detonation combustion system for a propulsion system, the rotating detonation combustion system defining a radial direction, a circumferential direction, and a longitudinal centerline in common with the propulsion system extended along a longitudinal direction. The rotating detonation combustion system includes an annular outer wall and an annular inner wall each generally concentric to the longitudinal centerline and together defining at least in part a combustion chamber and a combustion chamber inlet. The outer wall and the inner wall together define an annular nozzle concentric to the longitudinal centerline at the combustion chamber inlet. The nozzle defines a lengthwise direction and extending between a nozzle inlet and a nozzle outlet along the lengthwise direction, the nozzle inlet configured to receive a flow of oxidizer. The nozzle further defines a throat between the nozzle inlet and nozzle outlet. The rotating detonation combustion system further includes a fuel injection port defining a fuel outlet located between the nozzle inlet and the nozzle outlet for providing fuel to the flow of oxidizer received through the nozzle inlet.
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公开(公告)号：US12228282B2
公开(公告)日：2025-02-18
申请号：US18409690
申请日：2024-01-10
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Michael T. Bucaro , Ajoy Patra , Pradeep Naik , Perumallu Vukanti , R Narasimha Chiranthan , Clayton Stuart Cooper , Michael A. Benjamin , Steven C. Vise , Manampathy G. Giridharan , Krishnakumar Venkatesan
Abstract: An engine can utilize a combustor to combust fuel to drive the engine. A fuel nozzle assembly can supply fuel to the combustor for combustion or ignition of the fuel. The fuel nozzle assembly can include a swirler and a fuel nozzle to supply a mixture of fuel and air for combustion. The fuel nozzle can include both a primary and secondary fuel passage, and an additional air passage to provide for greater flame control, fuel provision, or local fuel and air mixing prior to combustion.
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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
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.
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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
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.
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