MX2015005799A - Aparato y metodo de combustion de ganancia de presion. - Google Patents

Aparato y metodo de combustion de ganancia de presion.

Info

Publication number
MX2015005799A
MX2015005799A MX2015005799A MX2015005799A MX2015005799A MX 2015005799 A MX2015005799 A MX 2015005799A MX 2015005799 A MX2015005799 A MX 2015005799A MX 2015005799 A MX2015005799 A MX 2015005799A MX 2015005799 A MX2015005799 A MX 2015005799A
Authority
MX
Mexico
Prior art keywords
combustion chamber
oxidant
communication
chamber
upstream
Prior art date
Application number
MX2015005799A
Other languages
English (en)
Other versions
MX365257B (es
Inventor
Juan Alejandro
Original Assignee
Exponential Tech Inc
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Exponential Tech Inc filed Critical Exponential Tech Inc
Publication of MX2015005799A publication Critical patent/MX2015005799A/es
Publication of MX365257B publication Critical patent/MX365257B/es

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C3/00—Combustion apparatus characterised by the shape of the combustion chamber
    • F23C3/006—Combustion apparatus characterised by the shape of the combustion chamber the chamber being arranged for cyclonic combustion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
    • F02K7/02—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof the jet being intermittent, i.e. pulse-jet
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C15/00—Apparatus in which combustion takes place in pulses influenced by acoustic resonance in a gas mass
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C3/00—Combustion apparatus characterised by the shape of the combustion chamber
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R7/00—Intermittent or explosive combustion chambers

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Fluidized-Bed Combustion And Resonant Combustion (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)
  • Combustion Of Fluid Fuel (AREA)

Abstract

Una cámara de combustión de ganancia de presión comprende una cámara de detonación, una cámara de pre-combustión, un generador de remolino de oxidante, una boquilla de expansióndeflexión (E-D), y una fuente de ignición. La cámara de detonación tiene un extremo de absorción ascendente y un extremo de descarga descendente, y se configura para permitir que un evento de combustión supersónico se propague a través de la misma. La cámara de pre-combustión tiene un extremo descendente en comunicación fluida con el extremo de absorción de cámara de detonación, un extremo ascendente en comunicación con un camino de entrega de combustible, y un perímetro circunferencial entre los extremos ascendente y descendente con una abertura anular en comunicación con un camino de entrega de oxidante anular. El generador de remolino de oxidante se ubica en el camino de entrega de oxidante y comprende veletas configuradas para causar que oxidante que fluye pasando las veletas para fluir tangencialmente en la cámara de pre-combustión así creando una zona de alta velocidad de remolino alrededor de la abertura anular y una zona de baja velocidad de remolino en una porción central de la cámara de precombustión. La boquilla de E-D se posiciona entre la cámara de precombustión y cámara de detonación y provee un camino de fluido difusivo entre las mismas. La fuente de ignición está en comunicación con la zona de baja velocidad de remolino de la cámara de pre-combustión. Esta configuración se espera que provea una cámara de combustión con una distancia y tiempo de DDT previos totales relativamente bajos, así permitiendo altas frecuencias de operación y alto desempeño correspondiente de la cámara de combustión.
MX2015005799A 2012-11-07 2013-11-07 Aparato y metodo de combustion de ganancia de presion. MX365257B (es)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US201261723667P 2012-11-07 2012-11-07
PCT/CA2013/050856 WO2014071525A1 (en) 2012-11-07 2013-11-07 Pressure-gain combustion apparatus and method

Publications (2)

Publication Number Publication Date
MX2015005799A true MX2015005799A (es) 2016-08-03
MX365257B MX365257B (es) 2019-05-27

Family

ID=50683880

Family Applications (1)

Application Number Title Priority Date Filing Date
MX2015005799A MX365257B (es) 2012-11-07 2013-11-07 Aparato y metodo de combustion de ganancia de presion.

Country Status (9)

Country Link
US (2) US10060618B2 (es)
EP (1) EP2917644A4 (es)
JP (1) JP6238997B2 (es)
CN (1) CN104919249B (es)
BR (1) BR112015010472A2 (es)
CA (1) CA2890151A1 (es)
MX (1) MX365257B (es)
RU (1) RU2660734C2 (es)
WO (1) WO2014071525A1 (es)

Families Citing this family (33)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11428413B2 (en) * 2016-03-25 2022-08-30 General Electric Company Fuel injection module for segmented annular combustion system
CN105972638B (zh) * 2016-05-26 2018-06-19 西北工业大学 一种回流式脉冲爆震燃烧室
CN106051821B (zh) * 2016-05-26 2018-08-28 西北工业大学 一种分流式多管脉冲爆震燃烧室
US20180010800A1 (en) * 2016-06-14 2018-01-11 Adithya Ananth NAGESH Shock compression based supersonic combustor
GB2560916B (en) * 2017-03-27 2020-01-01 Edwards Ltd Nozzle for an abatement device
US10627111B2 (en) 2017-03-27 2020-04-21 United Technologies Coproration Rotating detonation engine multi-stage mixer
US10436110B2 (en) 2017-03-27 2019-10-08 United Technologies Corporation Rotating detonation engine upstream wave arrestor
US11761635B2 (en) * 2017-04-06 2023-09-19 University Of Cincinnati Rotating detonation engines and related devices and methods
US10520195B2 (en) * 2017-06-09 2019-12-31 General Electric Company Effervescent atomizing structure and method of operation for rotating detonation propulsion system
CN107100735B (zh) * 2017-06-27 2018-11-20 哈尔滨工程大学 一种基于组合式燃烧室的船用燃气轮机
US11536456B2 (en) 2017-10-24 2022-12-27 General Electric Company Fuel and air injection handling system for a combustor of a rotating detonation engine
US20190242582A1 (en) * 2018-02-07 2019-08-08 General Electric Company Thermal Attenuation Structure For Detonation Combustion System
CN108844068B (zh) * 2018-09-03 2024-01-19 哈尔滨电气股份有限公司 一种全预混表面式燃烧器燃气空气掺混器
CN109209681A (zh) * 2018-10-08 2019-01-15 西北工业大学 一种回流式的脉冲爆震发动机爆震管结构
WO2020086681A2 (en) * 2018-10-23 2020-04-30 Sabic Global Technologies B.V. Method and reactor for conversion of hydrocarbons
CN109630277B (zh) * 2018-12-06 2021-01-15 西北工业大学 一种嵌入扰流装置的旋转爆震发动机
EP3980693B1 (en) * 2019-06-09 2023-11-22 Finno Energy Oy Method of controlling deflagration combustion process in pistonless combustor
CN110552813B (zh) * 2019-08-28 2024-05-03 中南大学 旋转切削式供粉系统及其粉末燃料冲压发动机
US10914274B1 (en) 2019-09-11 2021-02-09 General Electric Company Fuel oxygen reduction unit with plasma reactor
RU2724559C1 (ru) * 2019-09-19 2020-06-23 Публичное акционерное общество "ОДК-Уфимское моторостроительное производственное объединение ("ПАО "ОДК-УМПО") Турбореактивный авиационный двигатель
CN110778419B (zh) * 2019-10-14 2020-09-01 哈尔滨工程大学 用于爆轰燃烧室的起爆装置
US11773776B2 (en) 2020-05-01 2023-10-03 General Electric Company Fuel oxygen reduction unit for prescribed operating conditions
IT202000022396A1 (it) 2020-09-23 2022-03-23 Marelli Europe Spa Dispositivo riscaldatore per un sistema di scarico di un motore a combustione interna
US20220180855A1 (en) * 2020-12-08 2022-06-09 Igor Fridman Shock wave generator devices and systems
RU2762982C1 (ru) * 2021-03-15 2021-12-24 ОБЩЕСТВО С ОГРАНИЧЕННОЙ ОТВЕТСТВЕННОСТЬЮ "ВАСП ЭЙРКРАФТ" (ООО «Васп Эйркрафт») Способ приведения во вращение ротора с помощью реактивного двигателя
CN113154451B (zh) * 2021-04-27 2022-09-06 西北工业大学 一种旋转爆震燃烧室的导向喷管
CN114001375B (zh) * 2021-11-12 2022-09-06 西安热工研究院有限公司 一种带预燃燃烧室的旋转爆震燃烧室
PL439871A1 (pl) * 2021-12-16 2023-06-19 Sieć Badawcza Łukasiewicz-Instytut Lotnictwa Sposób oraz instalacja do podnoszenia temperatury dowolnego ze składników materiału pędnego silnika rakietowego do wyższej temperatury
US11619172B1 (en) * 2022-03-01 2023-04-04 General Electric Company Detonation combustion systems
CN114738117B (zh) * 2022-05-24 2023-06-20 厦门大学 一种基于特斯拉阀进气结构的地面旋转爆震发动机
CN115750138A (zh) * 2022-10-12 2023-03-07 哈尔滨工业大学 一种带尾喷管流道约束的环形旋转爆震发动机及设计方法
CN116557169B (zh) * 2023-07-10 2023-09-19 中国人民解放军空军工程大学 等离子体调控旋转爆震发动机工作模态的装置及方法
CN117469674B (zh) * 2023-12-26 2024-03-12 凯盛(漳州)新能源有限公司 一种光伏玻璃窑炉喷火枪装置

Family Cites Families (31)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SU66161A1 (ru) * 1944-12-20 1945-11-30 А.И. Болдырев Воздушно-реактивный двигатель пульсирующего действи
US3736747A (en) * 1971-07-09 1973-06-05 G Warren Combustor
SU459612A2 (ru) * 1973-06-01 1975-02-05 Харьковский авиационный институт Аэродинамический клапан дл камеры пульсирующего горени
SU840441A1 (ru) * 1977-07-05 1981-06-23 Казанский Ордена Трудового Красногознамени И Ордена Ленина Государ-Ственный Университет Им. Ульянова-Ленина Устройство релаксационного горени
US4262482A (en) * 1977-11-17 1981-04-21 Roffe Gerald A Apparatus for the premixed gas phase combustion of liquid fuels
JPS57187531A (en) * 1981-05-12 1982-11-18 Hitachi Ltd Low nox gas turbine burner
JPS60189708U (ja) * 1984-05-23 1985-12-16 東京瓦斯株式会社 パルス燃焼装置
EP0170895B1 (en) 1984-07-09 1989-03-22 Millipore Corporation Improved electrodeionization apparatus and method
CA1306873C (en) * 1987-04-27 1992-09-01 Jack R. Taylor Low coke fuel injector for a gas turbine engine
US6739852B1 (en) 1995-03-09 2004-05-25 Outland Technologies Usa, Inc. Rotary engine and method for determining engagement surface contours therefor
US5755196A (en) 1995-03-09 1998-05-26 Outland Design Technologies, Inc. Rotary positive displacement engine
AU6092098A (en) * 1996-12-28 1998-07-31 Aerostar Coatings, S.L. Self sustained detonation apparatus
US6497564B2 (en) 2000-01-07 2002-12-24 James B. Klassen Balanced rotors positive displacement engine and pump method and apparatus
US6705161B1 (en) 2000-08-08 2004-03-16 Outland Technologies (Usa), Inc. Positive displacement flow meter method and apparatus
US6505462B2 (en) 2001-03-29 2003-01-14 General Electric Company Rotary valve for pulse detonation engines
US7621118B2 (en) 2002-07-03 2009-11-24 Rolls-Royce North American Technologies, Inc. Constant volume combustor having a rotating wave rotor
CA2545485C (en) 2003-09-19 2009-11-10 Usfilter Corporation Apparatus and method for connecting water treatment devices
JP3994284B2 (ja) * 2004-02-19 2007-10-17 独立行政法人 宇宙航空研究開発機構 パルスデトネーションエンジン用バルブ
US7828546B2 (en) * 2005-06-30 2010-11-09 General Electric Company Naturally aspirated fluidic control for diverting strong pressure waves
KR101424784B1 (ko) * 2006-01-10 2014-07-31 가부시키가이샤 한도오따이 에네루기 켄큐쇼 표시장치 및 그의 제조방법
US7966803B2 (en) * 2006-02-03 2011-06-28 General Electric Company Pulse detonation combustor with folded flow path
US7758334B2 (en) * 2006-03-28 2010-07-20 Purdue Research Foundation Valveless pulsed detonation combustor
US20090139199A1 (en) * 2007-11-15 2009-06-04 General Electric Company Pulse detonation combustor valve for high temperature and high pressure operation
EP2267369A4 (en) * 2008-03-31 2014-11-26 Kawasaki Heavy Ind Ltd COOLING STRUCTURE FOR GAS TURBINE BURNER
US8544280B2 (en) * 2008-08-26 2013-10-01 Board Of Regents, The University Of Texas System Continuous detonation wave engine with quenching structure
US8602758B2 (en) 2008-09-17 2013-12-10 Exponential Technologies, Inc. Indexed positive displacement rotary motion device
JP5276500B2 (ja) * 2009-03-31 2013-08-28 株式会社眞誠 爆轟波発生装置
US20110073048A1 (en) * 2009-09-25 2011-03-31 Alejandro Juan Pressure gain combustion heat generator
US20110302904A1 (en) * 2010-06-11 2011-12-15 General Electric Company Pulsed Detonation Cleaning Device with Multiple Folded Flow Paths
RU2594845C2 (ru) * 2011-04-29 2016-08-20 Экспонентиал Текнолоджис, Инк. Устройство и способ управления установкой внутреннего сгорания с повышением давления
AU2012357567B2 (en) * 2011-12-19 2017-03-02 Exponential Technologies, Inc. Positive displacement expander

Also Published As

Publication number Publication date
JP2016503482A (ja) 2016-02-04
WO2014071525A1 (en) 2014-05-15
EP2917644A1 (en) 2015-09-16
RU2015120000A (ru) 2016-12-27
US20190093880A1 (en) 2019-03-28
EP2917644A4 (en) 2016-08-03
CN104919249A (zh) 2015-09-16
CA2890151A1 (en) 2014-05-15
JP6238997B2 (ja) 2017-11-29
BR112015010472A2 (pt) 2017-07-11
US20150300630A1 (en) 2015-10-22
RU2660734C2 (ru) 2018-07-09
MX365257B (es) 2019-05-27
US10060618B2 (en) 2018-08-28
CN104919249B (zh) 2017-12-22

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