WO2006057577A1 - Moteur à combustion à détonation intermittente - Google Patents

Moteur à combustion à détonation intermittente Download PDF

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Publication number
WO2006057577A1
WO2006057577A1 PCT/RU2005/000597 RU2005000597W WO2006057577A1 WO 2006057577 A1 WO2006057577 A1 WO 2006057577A1 RU 2005000597 W RU2005000597 W RU 2005000597W WO 2006057577 A1 WO2006057577 A1 WO 2006057577A1
Authority
WO
WIPO (PCT)
Prior art keywords
engine
detonation
nozzle
resonator
pulsating
Prior art date
Application number
PCT/RU2005/000597
Other languages
English (en)
Russian (ru)
Inventor
Anton Vladimirovich BORDOVSKY
Eduard Vasilievich Olkhovsky
Original Assignee
T Biznesa Obschestvo S Ogranic
Eduard Vasilievich Olkhovsky
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 T Biznesa Obschestvo S Ogranic, Eduard Vasilievich Olkhovsky filed Critical T Biznesa Obschestvo S Ogranic
Publication of WO2006057577A1 publication Critical patent/WO2006057577A1/fr

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Classifications

    • 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
    • F02K7/04—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 with resonant combustion chambers
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/24—Three-dimensional ellipsoidal
    • F05D2250/241—Three-dimensional ellipsoidal spherical

Definitions

  • SUBSTANCE invention relates to pulsating airborne reactive detonation combustion engines and can be used, for example, as a gas-jet electric generator engine or an aircraft with subsonic flight speeds, in particular, a helicopter.
  • the closest in principle of operation and technical execution is the device according to the patent of the Russian Federation Na 2034996, containing a housing, a combustion chamber with an input, an annular channel with an input and an output, a converter of the internal energy of the working fluid into mechanical work of the traction force in the form of a gas-dynamic resonator, an engine nozzle, a mechanism initiation of detonation and an annular nozzle for supplying a fuel mixture (3).
  • this engine also has the above disadvantages.
  • the present invention is the maximum reduction in weight and weight under the action of significant centrifugal forces, and the result is an increase in the efficiency and reliability of the engine in these conditions.
  • a pulsating detonation combustion engine including a housing and a combustion chamber with an input, an annular channel with an input and an output, a converter of the internal energy of the working fluid into mechanical work of the traction force in the form of a gas-dynamic resonator, an engine nozzle, a detonation initiation mechanism, and an annular nozzle for supplying a fuel mixture, characterized in that the combustion chamber is made in the form of a hemispherical gas-dynamic resonator and engine nozzles, the detonation initiation mechanism is made in the form of a tube plugged on one side, the free output of which is connected to the center of the gas-dynamic resonator, while the following relations are observed:
  • Vi is the velocity of detonation products
  • R is the radius of the annular supersonic nozzle 9.
  • the pulsating engine is characterized in that the engine is equipped with a hemispherical cavitator rotating by means of an impeller, located behind, with a gap, a gas-dynamic resonator, while the impeller is mounted on the outer surface of the cavitator.
  • a pulsating motor is characterized in that the cavitator is mounted in a bearing assembly located on the resonator.
  • the pulsating engine is characterized in that the engine is equipped with an air pipe for supplying air located on the engine housing radially in the plane of rotation of the working body.
  • a pulsating motor is characterized by the fact that the air pipe has a centrifugal switch.
  • the pulsating motor is characterized in that the centrifugal switch has a locking spring located in a support on the inner surface of the nozzle, and guides for moving it along the inner surface of the air nozzle.
  • the pulsating engine is characterized in that the air pipe has openings for air intake from the atmosphere.
  • a pulsating motor is characterized in that the nozzle has a high pressure air shutoff.
  • FIG. 1 is a general diagram
  • FIG. 2 is a system for supplying an engine with air
  • FIG. 3 is a section along A-A of FIG. 2.
  • the engine is mounted on a working body (a helicopter blade or an electric generator rod) and works as follows.
  • the high-pressure air (VVD), gas (for example, methane) and high voltage on the ignition plug 7 are simultaneously turned on.
  • the VVD enters the air pipe 11 located inside the working body (blades or rod not shown), where the air pressure drops to low due to a significantly larger nozzle cross-section.
  • the lower part of the pipe 11 is closed by a spring lock, consisting of a support for the spring 17, spring 13, centrifugal lock 14 and the annular nozzle 16.
  • Air through the pipe enters the engine housing 4 and, mixed with fuel (gas), flows out through the rotating impeller 3, which leads in rotation, the hemispherical cavitator 6 on the bearing assembly 5.
  • Part of the fuel is also fed into the cavity of the reactor 8, where in cavitation vortices (including cold state) it is partially subjected to pyrolysis.
  • Pyrolysis products are mixed with the air-fuel mixture w and through the annular supersonic nozzle 9 into the combustion chamber, which consists of the resonator 1 and the nozzle 2.
  • the combustion chamber which consists of the resonator 1 and the nozzle 2.
  • Detonation products both direct and reflected from the resonator 1 through the nozzle 2, flow into the atmosphere.
  • a new portion of the air-fuel mixture from the annular supersonic nozzle 9 enters the resulting reduced pressure region. Reflected in the detonation initiation mechanism 10, made in this case in the form of a tube, the pressure pulse acts on the nausea-air mixture, and the process repeats.
  • the engine is equipped with a hemispherical cavitator rotating through the impeller, located behind the gas-dynamic resonator, with a gap (the impeller is mounted on the outer surface of the cavitator and promotes high-quality mixing of the fuel mixture).
  • the resonator 1 heats up above 700 0 C, which facilitates the pyrolysis of fuel in reactor 8.
  • reactor 8 in the cavitation vortices rotating at a speed of more than one million revolutions per minute, part of the fuel is pyrolyzed, which improves the detonation conditions.
  • the centrifugal switch 14 overcomes the blocking effect of the spring 13 and opens the hole 16, closing the intake of the VVD. Air from the atmosphere through the intake openings 15 enters the pipe 11, where, under the action of centrifugal forces, it is compressed, ensuring the operation of the engine, while the air pipe 11 acts as a centrifugal radial compressor.
  • the centrifugal switch 14 has a locking spring 13 located in the support 17 on the inner surface of the air pipe 11.
  • the design of the pulsating detonation combustion engine is characterized by the following ratios: Vi / V 2 ⁇ 2L / R, where
  • Vi is the velocity of the detonation products
  • V g is the feed rate of the fuel mixture
  • R is the radius of the annular supersonic nozzle 9.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Fuel-Injection Apparatus (AREA)

Abstract

La présente invention se rapporte à un moteur à combustion à détonation intermittente, qui comprend un corps dans lequel sont logés une chambre de combustion dotée d'un orifice d'entrée, un canal annulaire doté d'un orifice d'entrée et d'un orifice de sortie, un convertisseur destiné à transformer l'énergie interne du fluide actif en l'action mécanique d'une force de traction et se présentant sous la forme d'un résonateur à dynamique gazeuse (1), un mécanisme d'amorçage de détonation (10), et une buse annulaire (9) destinée à fournir le mélange de carburant. La chambre de combustion se présente sous la forme d'un résonateur à dynamique gazeuse semi-sphérique (1) et d'une tuyère (2) de moteur. Le mécanisme d'amorçage de détonation (10) se présente sous la forme de tuyaux, fermés à une extrémité et dont l'extrémité libre est reliée au centre du résonateur à dynamique gazeuse semi-sphérique (1). Dans le moteur selon l'invention, la relation V1/V2≤2L/R est respectée, où V1 représente la vitesse des produits de détonation, V2 représente la vitesse d'alimentation en mélange de carburant, 2L représente deux longueurs du mécanisme d'amorçage de détonation et le rayon du résonateur, et R représente le rayon de la tuyère ultrasonore annulaire. L'invention permet de réduire la masse et les dimensions globales du moteur dans des conditions de forces centrifuges importantes, et d'améliorer la fiabilité et l'efficacité d'un moteur dans lesdites conditions.
PCT/RU2005/000597 2004-11-22 2005-11-17 Moteur à combustion à détonation intermittente WO2006057577A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
RU2004133912/06A RU2282044C1 (ru) 2004-11-22 2004-11-22 Пульсирующий двигатель детонационного горения
RU2004133912 2004-11-22

Publications (1)

Publication Number Publication Date
WO2006057577A1 true WO2006057577A1 (fr) 2006-06-01

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Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/RU2005/000597 WO2006057577A1 (fr) 2004-11-22 2005-11-17 Moteur à combustion à détonation intermittente

Country Status (2)

Country Link
RU (1) RU2282044C1 (fr)
WO (1) WO2006057577A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2011155248A1 (fr) * 2010-06-10 2011-12-15 学校法人早稲田大学 Moteur
CN110173374A (zh) * 2019-05-14 2019-08-27 西北工业大学 一种基于虹膜光圈原理的变阻塞比爆震管

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2013109079A (ru) * 2010-07-19 2014-09-10 Некоммерческое партнерство по научной, образовательной и инновационной деятельности "Центр импульсно-детонационного горения" Устройство для передачи детонации
RU2487256C2 (ru) * 2011-03-31 2013-07-10 Федеральное государственное бюджетное образовательное учреждение высшего профессионального образования "Московский государственный университет имени М.В. Ломоносова" (МГУ) Способ детонационного сжигания водорода в стационарном сверхзвуковом потоке
RU2489595C1 (ru) * 2011-11-24 2013-08-10 Александр Юрьевич Соколов Тяговый модуль постоянного детонационного горения паровоздушной топливной смеси
RU2526613C1 (ru) * 2013-02-27 2014-08-27 Государственное Научное Учреждение "Институт Тепло- И Массообмена Имени А.В. Лыкова Национальной Академии Наук Беларуси" Пульсирующая детонационная установка для создания силы тяги
RU2718726C1 (ru) * 2018-11-29 2020-04-14 Общество с ограниченной ответственностью "Новые физические принципы" Способ работы импульсно-детонационного двигателя в поле центробежных сил и устройство для его реализации в реактивном вертолёте
RU2752817C1 (ru) 2020-12-16 2021-08-06 Общество с ограниченной ответственностью «Васп Эйркрафт» Пульсирующий детонационный реактивный двигатель
RU207457U1 (ru) * 2021-07-26 2021-10-28 Общество С Ограниченной Ответственностью "Пульсирующие Детонационные Технологии" Выходное устройство двигателя прямой реакции

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3824787A (en) * 1970-07-16 1974-07-23 A Etessam Intermittent combustion device with a pair of coextensive and coaxial mutually inductive chambers
RU2034996C1 (ru) * 1993-10-11 1995-05-10 Владимир Федорович Антоненко Способ получения тяги и устройство для его осуществления
RU2066779C1 (ru) * 1993-06-10 1996-09-20 Саратовская научно-производственная фирма "Растр" Реактивное сопло пульсирующего двигателя детонационного горения с центральным телом
RU2078974C1 (ru) * 1993-12-14 1997-05-10 Саратовская научно-производственная фирма "Растр" Регулируемая детонационная камера пульсирующего реактивного двигателя

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3824787A (en) * 1970-07-16 1974-07-23 A Etessam Intermittent combustion device with a pair of coextensive and coaxial mutually inductive chambers
RU2066779C1 (ru) * 1993-06-10 1996-09-20 Саратовская научно-производственная фирма "Растр" Реактивное сопло пульсирующего двигателя детонационного горения с центральным телом
RU2034996C1 (ru) * 1993-10-11 1995-05-10 Владимир Федорович Антоненко Способ получения тяги и устройство для его осуществления
RU2078974C1 (ru) * 1993-12-14 1997-05-10 Саратовская научно-производственная фирма "Растр" Регулируемая детонационная камера пульсирующего реактивного двигателя

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2011155248A1 (fr) * 2010-06-10 2011-12-15 学校法人早稲田大学 Moteur
JP5737632B2 (ja) * 2010-06-10 2015-06-17 学校法人早稲田大学 エンジン
US10125674B2 (en) 2010-06-10 2018-11-13 Waseda University Engine
CN110173374A (zh) * 2019-05-14 2019-08-27 西北工业大学 一种基于虹膜光圈原理的变阻塞比爆震管
CN110173374B (zh) * 2019-05-14 2021-03-26 西北工业大学 一种基于虹膜光圈原理的变阻塞比爆震管

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Publication number Publication date
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