WO2011037597A1 - A system and method of combustion for sustaining a continuous detonation wave with transient plasma - Google Patents
A system and method of combustion for sustaining a continuous detonation wave with transient plasma Download PDFInfo
- Publication number
- WO2011037597A1 WO2011037597A1 PCT/US2009/068630 US2009068630W WO2011037597A1 WO 2011037597 A1 WO2011037597 A1 WO 2011037597A1 US 2009068630 W US2009068630 W US 2009068630W WO 2011037597 A1 WO2011037597 A1 WO 2011037597A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- recited
- combustion chamber
- detonation wave
- high voltage
- voltage pulses
- Prior art date
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
- F02K9/62—Combustion or thrust chambers
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
- F02K9/62—Combustion or thrust chambers
- F02K9/66—Combustion or thrust chambers of the rotary type
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/14—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
-
- 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
-
- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05H—PLASMA TECHNIQUE; PRODUCTION OF ACCELERATED ELECTRICALLY-CHARGED PARTICLES OR OF NEUTRONS; PRODUCTION OR ACCELERATION OF NEUTRAL MOLECULAR OR ATOMIC BEAMS
- H05H1/00—Generating plasma; Handling plasma
- H05H1/24—Generating plasma
- H05H1/52—Generating plasma using exploding wires or spark gaps
-
- 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
- F05D2250/25—Three-dimensional helical
-
- 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
- F05D2270/00—Control
- F05D2270/01—Purpose of the control system
- F05D2270/17—Purpose of the control system to control boundary layer
- F05D2270/172—Purpose of the control system to control boundary layer by a plasma generator, e.g. control of ignition
Definitions
- the present disclosure relates to a Continuous Detonation Wave Engine, and more particularly to sustainment of a spinning detonation wave thereof.
- Continuous Detonation Wave Engines generate a spinning detonation wave in an annular combustion chamber. Sustainment of the spinning detonation wave may be difficult as numerous factors will tend to damp and dissipate the spinning detonation wave.
- Figure 1 is a general schematic view of a Continuous Detonation Wave Engine
- Figure 2 is a general schematic view of a Continuous Detonation Wave Engine illustrating a spinning detonation wave.
- FIG. 1 schematically illustrates a Continuous Detonation Wave Engine (CDWE) 20.
- the CDWE 20 provides a compact and efficient system which enables relatively low feed pressure and high combustion efficiency. CDWEs provide for high energy utilization.
- the CDWE 20 generally includes an annular combustion chamber 22 defined by an outer wall structure 24 and an inner wall structure 26.
- the annular combustion chamber 22 is closed on one end section by an injector system 28 which communicates with a propellant system 30 which supplies propellants such as a fuel and an oxidizer which form a reacting mixture.
- the reacting mixture is created by intimately mixing the propellants by the injector system 28.
- One injector system 28 may have a geometry selected based on the degree of mixing.
- the geometry of the injector system 28 may include impinging jets, swirl elements, pre- mixing chamber and other features that provide for intimate mixing of the propellants.
- the fuel includes Ethylene and the oxidizer includes oxygen.
- the annular combustion chamber 22 is open opposite the injector system 28 to define a nozzle 32.
- an initiation system 34 is utilized to ignite the spinning detonation wave.
- an initiation system 34 may include a mixing chamber 36, a spark plug 38 and a tangential detonation tube 40.
- the initiation system 34 may use devices to ignite combustion including a pyrotechnic ignitor, a glow plug, hypergols, and pyrophoric fluids and others in lieu of or in addition to the spark plug 38.
- the initiation system 34 may include detonation cord, exploding wires, and/or a local ignition system disposed proximate the injector.
- a relatively small amount of propellants are premixed in the mixing chamber 36, the spark plug 38 lights off the propellants, then the burning mixture (deflagration) transitions to a detonation wave within the tangential detonation tube 40.
- the tangential detonation tube 40 injects the detonation wave tangentially into the annular combustion chamber 22 to initiate the spinning detonation wave. It should be understood that alternate or additional components may be utilized with the initiation system. Once the process is started, no additional ignition energy is typically required and the initiation system 34 may be shut down.
- the propellants burn to form at least one transversal or spinning detonation wave that propagates normally in an azimuthal direction from the axially injected propellants within the annular combustion chamber 22 as generally understood ( Figure 2).
- the spinning detonation wave propagates along the rotating detonation front and burns a shock-compressed mixture.
- the spinning detonation wave within the annular combustion chamber 22 provide for increased chemical energy utilization relative to conventional constant pressure combustion.
- the CDWE 20 due in part to the more efficient thermodynamic properties, exhibits a higher level of performance than more conventional propulsion system that rely on constant-pressure combustion processes. Sustainment of the spinning detonation wave may be relatively difficult and sensitive to the operational environment. Numerous factors tend to damp and dissipate the spinning detonation wave to include poorly mixed propellants, unreacted propellants, improper injection velocities, chemical kinetics, wall heat transfer, boundary layer build-up, etc.
- a transient plasma system 42 also known as a nanosecond pulsed plasma system, is located within the CDWE 20 to sustain the spinning detonation wave.
- the transient plasma system 42 includes a cathode 44 in the outer wall structure 24 and an anode 46 in the inner wall structure 26 or vice-versa such that electrical potential is disposed between the outer wall structure 24 and the inner wall structure 26 within the annular combustion chamber 22.
- a pulse generator 48 operates to generate low energy but intense, high voltage pulses to provide transient plasma P, wherein electrons at high velocity travel through the annular combustion chamber 22. In one example, the pulse is 20 nsec at 10 - 100 kV.
- the transient plasma P causes high velocity electrons and streamers to be created.
- the high velocity electrons and streamers produce radicals, ions and a high proportion of vibrationally excited chemical species which thereby increase reaction rates.
- the transient plasma P also greatly increase the reactivity of chemical species, via radical formation and ionization, and thus minimize the damping effect of chemical kinetics on the spinning detonation wave. The increase in chemical reaction rates augments and sustains the detonation process.
- Arc discharge is prevented based on the very rapid pulsing of the voltage field. In this regard, there is substantially precluded loss of velocity with the electrons.
- This configuration enables the CDWE 20 to be insensitive to design and operating environment variables and thereby perform with increased energy release as compared to constant pressure configured engines.
- the transient plasma system 42 enables engines and burners with an approximate 37% increase in energy utilization over conventional constant pressure engine and burners. This translates into an approximately 17% increase in specific impulse for reaction propulsion systems.
- the transient plasma system 42 will facilitate sustainment of the spinning detonation wave without the requirement of supplemental oxygen.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Plasma & Fusion (AREA)
- Spectroscopy & Molecular Physics (AREA)
- Ignition Installations For Internal Combustion Engines (AREA)
- Plasma Technology (AREA)
- Fluidized-Bed Combustion And Resonant Combustion (AREA)
Abstract
Description
Claims
Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
RU2012115531/06A RU2537659C2 (en) | 2009-09-23 | 2009-12-18 | System and method of combustion for support of continuous detonation wave with nonstationary plasma |
JP2012530855A JP5764131B2 (en) | 2009-09-23 | 2009-12-18 | Combustion system and method for maintaining a continuous detonation wave using a transient plasma |
US13/392,149 US9046058B2 (en) | 2009-09-23 | 2009-12-18 | System and method of combustion for sustaining a continuous detonation wave with transient plasma |
EP09838546.1A EP2480771B1 (en) | 2009-09-23 | 2009-12-18 | A system and method of combustion for sustaining a continuous detonation wave with transient plasma |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US24503409P | 2009-09-23 | 2009-09-23 | |
US61/245,034 | 2009-09-23 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2011037597A1 true WO2011037597A1 (en) | 2011-03-31 |
Family
ID=42635078
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/US2009/068630 WO2011037597A1 (en) | 2009-09-23 | 2009-12-18 | A system and method of combustion for sustaining a continuous detonation wave with transient plasma |
Country Status (5)
Country | Link |
---|---|
US (1) | US9046058B2 (en) |
EP (1) | EP2480771B1 (en) |
JP (2) | JP5764131B2 (en) |
RU (1) | RU2537659C2 (en) |
WO (1) | WO2011037597A1 (en) |
Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2525062A1 (en) * | 2011-05-16 | 2012-11-21 | MBDA France | Turbomachine with detonation chamber and aircraft provided with such a turbomachine |
WO2014189603A3 (en) * | 2013-03-15 | 2015-04-02 | Rolls-Royce North American Technologies, Inc. | Continuous detonation combustion engine and system |
US20150308348A1 (en) * | 2013-05-22 | 2015-10-29 | United Technologies Corporation | Continuous detonation wave turbine engine |
RU2620736C1 (en) * | 2015-12-28 | 2017-05-29 | Открытое акционерное общество "Уфимское моторостроительное производственное объединение" ОАО "УМПО" | Method of organising working process in turbojet engine with continuously-detonating combustion chamber and device for its implementation |
RU184207U1 (en) * | 2018-02-28 | 2018-10-18 | Закрытое акционерное общество "Институт телекоммуникаций" | RESONANT AIR-REACTIVE ENGINE |
US11493207B2 (en) | 2017-04-30 | 2022-11-08 | King Abdullah University Of Science And Technology | Auto-driven plasma actuator for transition from deflagration to detonation combustion regime and method |
Families Citing this family (21)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2014129920A1 (en) * | 2013-02-19 | 2014-08-28 | Некоммерческое Партнерство По Научной, Образовательной И Инновационной Деятельности "Центр Импульсного Детонационного Горения" | Device for fuel combustion in a continuous detonation wave |
US9732670B2 (en) | 2013-12-12 | 2017-08-15 | General Electric Company | Tuned cavity rotating detonation combustion system |
WO2020006212A1 (en) * | 2018-06-28 | 2020-01-02 | Clearsign Combustion Corporation | Combustion system including a combustion sensor and a plasma generator |
FR3051508B1 (en) * | 2016-05-23 | 2018-06-15 | Safran | ANNULAR COMBUSTION CHAMBER WITH CONTINUOUS WAVE WAVE |
US20180080412A1 (en) | 2016-09-22 | 2018-03-22 | Board Of Regents, The University Of Texas System | Systems, apparatuses and methods for improved rotating detonation engines |
US10436110B2 (en) | 2017-03-27 | 2019-10-08 | United Technologies Corporation | Rotating detonation engine upstream wave arrestor |
US10627111B2 (en) | 2017-03-27 | 2020-04-21 | United Technologies Coproration | Rotating detonation engine multi-stage mixer |
US11761635B2 (en) * | 2017-04-06 | 2023-09-19 | University Of Cincinnati | Rotating detonation engines and related devices and methods |
US11674476B2 (en) * | 2017-06-09 | 2023-06-13 | General Electric Company | Multiple chamber rotating detonation combustor |
US20180356094A1 (en) * | 2017-06-09 | 2018-12-13 | General Electric Company | Variable geometry rotating detonation combustor |
US10969107B2 (en) | 2017-09-15 | 2021-04-06 | General Electric Company | Turbine engine assembly including a rotating detonation combustor |
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 |
US11149954B2 (en) | 2017-10-27 | 2021-10-19 | General Electric Company | Multi-can annular rotating detonation combustor |
CN109967460B (en) * | 2019-04-01 | 2020-07-07 | 中国人民解放军战略支援部队航天工程大学 | Engine nozzle carbon deposition removing method based on low-temperature plasma |
RU2737322C2 (en) * | 2019-04-26 | 2020-11-27 | Федеральное государственное унитарное предприятие "Центральный аэрогидродинамический институт имени профессора Н.Е. Жуковского" | Detonation engine operation method and device for its implementation |
RU2724557C1 (en) * | 2019-06-21 | 2020-06-23 | Публичное акционерное общество "ОДК - Уфимское моторостроительное производственное объединение" (ПАО "ОДК-УМПО") | Operating method of straight-flow air-jet engine and device for implementation thereof |
RU2724558C1 (en) * | 2019-06-21 | 2020-06-23 | Публичное акционерное общество "ОДК - Уфимское моторостроительное производственное объединение" (ПАО "ОДК-УМПО") | Method and device for arrangement of periodic operation of continuous-detonation combustion chamber |
CN110778419B (en) * | 2019-10-14 | 2020-09-01 | 哈尔滨工程大学 | Detonating device for detonation combustor |
CN114001376B (en) * | 2021-11-23 | 2023-03-14 | 中国人民解放军空军工程大学 | Gas collection cavity plasma activation explosion-assisted rotary detonation combustion chamber |
WO2023171681A1 (en) * | 2022-03-07 | 2023-09-14 | Pdエアロスペース株式会社 | Combustion mode switching engine |
CN116557169B (en) * | 2023-07-10 | 2023-09-19 | 中国人民解放军空军工程大学 | Device and method for regulating and controlling working mode of rotary detonation engine by using plasma |
Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3336754A (en) * | 1966-03-21 | 1967-08-22 | Oswald H Lange | Continuous detonation reaction engine |
US20090158748A1 (en) * | 2007-12-21 | 2009-06-25 | United Technologies Corporation | Direct induction combustor/generator |
Family Cites Families (56)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4097820A (en) | 1972-01-26 | 1978-06-27 | Rolls-Royce Limited | Lasers |
US3954380A (en) | 1974-09-16 | 1976-05-04 | Alexandr Alexandrovich Valaev | Method and apparatus for intermittent combustion |
US4215635A (en) | 1978-12-14 | 1980-08-05 | The United States Of America As Represented By The Secretary Of The Army | Safe and arming device |
US4365471A (en) * | 1979-11-05 | 1982-12-28 | Adams Joseph S | Compression wave former |
IL82200A (en) | 1987-04-13 | 1996-01-31 | Rom Josef | Method and apparatus for launching a projectile at hypersonic velocity |
US5262206A (en) | 1988-09-20 | 1993-11-16 | Plasma Technik Ag | Method for making an abradable material by thermal spraying |
US5019686A (en) | 1988-09-20 | 1991-05-28 | Alloy Metals, Inc. | High-velocity flame spray apparatus and method of forming materials |
US5206059A (en) | 1988-09-20 | 1993-04-27 | Plasma-Technik Ag | Method of forming metal-matrix composites and composite materials |
US5187319A (en) | 1990-09-20 | 1993-02-16 | Societe Nationale Des Poudres Et Explosifs | Low vulnerability component of explosive ammunition and process for initiating a charge of low-sensitivity composite explosive |
US5261327A (en) | 1992-01-29 | 1993-11-16 | Patrick Carney | Blasting method and composition |
RU2066426C1 (en) * | 1993-12-14 | 1996-09-10 | Саратовская научно-производственная фирма "Растр" | Detonation chamber |
ZA953386B (en) | 1994-05-02 | 1996-01-12 | Robert Oliver Hill | A fuse and a method of manufacturing it |
JPH0874731A (en) * | 1994-09-07 | 1996-03-19 | Ishikawajima Harima Heavy Ind Co Ltd | Propulsion device for space craft |
DE59506236D1 (en) | 1995-02-02 | 1999-07-22 | Sulzer Innotec Ag | Non-slip composite coating |
US6001426A (en) | 1996-07-25 | 1999-12-14 | Utron Inc. | High velocity pulsed wire-arc spray |
US6124563A (en) | 1997-03-24 | 2000-09-26 | Utron Inc. | Pulsed electrothermal powder spray |
US6152010A (en) | 1998-04-27 | 2000-11-28 | The United States Of America As Represented By The Secretary Of The Navy | Wide-area slurry mine clearance |
US6734172B2 (en) | 1998-11-18 | 2004-05-11 | Pacific Northwest Research Institute | Surface receptor antigen vaccines |
RU2157909C1 (en) * | 1999-05-26 | 2000-10-20 | Центральный институт авиационного моторостроения им. П.И. Баранова | Supersonic pulse detonating ramjet engine and method of its functioning |
US6637255B2 (en) | 2000-01-06 | 2003-10-28 | The Johns Hopkins University | Damped paddle wheel for plasma chamber shock tube |
US6666018B2 (en) | 2000-03-31 | 2003-12-23 | General Electric Company | Combined cycle pulse detonation turbine engine |
US6442930B1 (en) | 2000-03-31 | 2002-09-03 | General Electric Company | Combined cycle pulse detonation turbine engine |
US20050187581A1 (en) | 2000-12-18 | 2005-08-25 | Hakuju Institute For Health Science, Co., Ltd. | Methods of treating disorders with electric fields |
US6453660B1 (en) * | 2001-01-18 | 2002-09-24 | General Electric Company | Combustor mixer having plasma generating nozzle |
US20030209198A1 (en) | 2001-01-18 | 2003-11-13 | Andrew Shabalin | Method and apparatus for neutralization of ion beam using ac or dc ion source |
US20020197885A1 (en) | 2001-06-22 | 2002-12-26 | Jack Hwang | Method of making a semiconductor transistor by implanting ions into a gate dielectric layer thereof |
EP1319423A3 (en) | 2001-12-11 | 2003-10-08 | Dornier Medtech System GmbH | Apparatus and method for initiating chemical reactions and for the targeted delivery of drugs or other agents |
WO2003068672A2 (en) | 2002-02-12 | 2003-08-21 | Kionix, Inc. | Fabrication of ultra-shallow channels for microfluidic devices and systems |
US7288892B2 (en) | 2002-03-12 | 2007-10-30 | Board Of Trustees Of The Leland Stanford Junior University | Plasma display panel with improved cell geometry |
US6725646B2 (en) | 2002-04-10 | 2004-04-27 | Caterpillar Inc | Rotary pulse detonation engine |
US7310951B2 (en) | 2002-04-19 | 2007-12-25 | Hokkaido Technology Licensing Office Co., Ltd. | Steady-state detonation combustor and steady-state detonation wave generating method |
US7032924B2 (en) | 2003-06-24 | 2006-04-25 | Autoliv Asp, Inc. | Electrically controlled airbag inflator apparatus and method |
US6964171B2 (en) | 2003-09-11 | 2005-11-15 | The United States Of America As Represented By The Secretary Of The Navy | Method and apparatus using jets to initiate detonations |
US7095179B2 (en) | 2004-02-22 | 2006-08-22 | Zond, Inc. | Methods and apparatus for generating strongly-ionized plasmas with ionizational instabilities |
US7663319B2 (en) | 2004-02-22 | 2010-02-16 | Zond, Inc. | Methods and apparatus for generating strongly-ionized plasmas with ionizational instabilities |
JP4256820B2 (en) * | 2004-06-29 | 2009-04-22 | 三菱重工業株式会社 | Detonation engine and aircraft equipped with the same |
US7449068B2 (en) | 2004-09-23 | 2008-11-11 | Gjl Patents, Llc | Flame spraying process and apparatus |
US7183515B2 (en) | 2004-12-20 | 2007-02-27 | Lockhead-Martin Corporation | Systems and methods for plasma jets |
US7530265B2 (en) | 2005-09-26 | 2009-05-12 | Baker Hughes Incorporated | Method and apparatus for elemental analysis of a fluid downhole |
US20070113781A1 (en) | 2005-11-04 | 2007-05-24 | Lichtblau George J | Flame spraying process and apparatus |
JP4674193B2 (en) | 2005-11-22 | 2011-04-20 | 日本特殊陶業株式会社 | Ignition control method for plasma jet spark plug and ignition device using the method |
US20070184554A1 (en) | 2005-12-01 | 2007-08-09 | Nps Allelix Corp. | Biomarker of improved intestinal function |
US20070137172A1 (en) * | 2005-12-16 | 2007-06-21 | General Electric Company | Geometric configuration and confinement for deflagration to detonation transition enhancement |
US7685806B2 (en) * | 2005-12-29 | 2010-03-30 | General Electric Company | Method and apparatus for supersonic and shock noise reduction in aircraft engines using pneumatic corrugations |
RU60144U1 (en) * | 2006-09-06 | 2007-01-10 | Виталий Николаевич Федорец | DETONATION ENGINE WITH MAGNETIC-DYNAMIC CONTROL DEVICE |
RU60145U1 (en) * | 2006-09-06 | 2007-01-10 | Виталий Николаевич Федорец | KNOCKING ENGINE WITH ELECTROMAGNETIC CONTROL DEVICE |
US7748211B2 (en) | 2006-12-19 | 2010-07-06 | United Technologies Corporation | Vapor cooling of detonation engines |
US8082725B2 (en) * | 2007-04-12 | 2011-12-27 | General Electric Company | Electro-dynamic swirler, combustion apparatus and methods using the same |
WO2008154222A1 (en) | 2007-06-06 | 2008-12-18 | Mks Instruments, Inc. | Particle reduction through gas and plasma source control |
RU2347098C1 (en) * | 2007-06-13 | 2009-02-20 | Институт теоретической и прикладной механики им. С.А. Христиановича Сибирское отделение Российской академии наук (ИТПМ СО РАН) | Method for operation of supersonic pulse athodyd and supersonic pulse athodyd |
US20080311612A1 (en) | 2007-06-15 | 2008-12-18 | Pioneer Hi-Bred International, Inc. | Functional Expression of Higher Plant Nitrate Transporters in Pichia Pastoris |
JP2009026779A (en) | 2007-07-17 | 2009-02-05 | Hitachi High-Technologies Corp | Vacuum treatment apparatus |
US20090231583A1 (en) | 2007-09-14 | 2009-09-17 | Roger Smith | Local non-perturbative remote sensing devices and method for conducting diagnostic measurements of magnetic and electric fields of optically active mediums |
US7599062B2 (en) | 2007-09-14 | 2009-10-06 | Roger Smith | Local non-perturbative remote sensing devices and method for conducting diagnostic measurements of magnetic and electric fields of optically active mediums |
DE102007056502B4 (en) | 2007-11-22 | 2010-07-29 | Eads Deutschland Gmbh | Method and device for building up residual stresses in a metallic workpiece |
US8082728B2 (en) * | 2008-02-01 | 2011-12-27 | General Electric Company | System and method of continuous detonation in a gas turbine engine |
-
2009
- 2009-12-18 JP JP2012530855A patent/JP5764131B2/en active Active
- 2009-12-18 WO PCT/US2009/068630 patent/WO2011037597A1/en active Application Filing
- 2009-12-18 RU RU2012115531/06A patent/RU2537659C2/en active
- 2009-12-18 US US13/392,149 patent/US9046058B2/en active Active
- 2009-12-18 EP EP09838546.1A patent/EP2480771B1/en active Active
-
2015
- 2015-04-27 JP JP2015089927A patent/JP6055021B2/en active Active
Patent Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3336754A (en) * | 1966-03-21 | 1967-08-22 | Oswald H Lange | Continuous detonation reaction engine |
US20090158748A1 (en) * | 2007-12-21 | 2009-06-25 | United Technologies Corporation | Direct induction combustor/generator |
Non-Patent Citations (2)
Title |
---|
BYKOVSKII F A ET AL: "Realization and modeling of continuous spin detonation of a hydrogen-oxygen mixture in flow-type combustors. 1. Combustors of cylindrical annular geometry", COMBUSTION, EXPLOSION, AND SHOCK WAVES, KLUWER ACADEMIC PUBLISHERS-PLENUM PUBLISHERS, NE, vol. 45, no. 5, 10 November 2009 (2009-11-10), pages 606 - 617, XP019787919, ISSN: 1573-8345 * |
WANG F ET AL: "Transient plasma ignituion of hydrocarbon-air mixtures in pulse detonation engines", 1 January 2004, AIAA AEROSPACE SCIENCES MEETING / AIAA THERMOPHYSICS CONFERENCE, XX, XX, PAGE(S) 1 - 8, XP009138055 * |
Cited By (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2525062A1 (en) * | 2011-05-16 | 2012-11-21 | MBDA France | Turbomachine with detonation chamber and aircraft provided with such a turbomachine |
WO2012156597A1 (en) * | 2011-05-16 | 2012-11-22 | Mbda France | Turbine engine including a detonation chamber and aircraft provided with such a turbine engine |
FR2975434A1 (en) * | 2011-05-16 | 2012-11-23 | Mbda France | TURBOMACHINE WITH DETONATION CHAMBER AND FLYWHEEL EQUIPPED WITH SUCH A TURBOMACHINE |
JP2014517194A (en) * | 2011-05-16 | 2014-07-17 | エムベーデーアー フランス | Turbo engine with detonation chamber and flying vehicle equipped with turbo engine |
WO2014189603A3 (en) * | 2013-03-15 | 2015-04-02 | Rolls-Royce North American Technologies, Inc. | Continuous detonation combustion engine and system |
US9512805B2 (en) | 2013-03-15 | 2016-12-06 | Rolls-Royce North American Technologies, Inc. | Continuous detonation combustion engine and system |
US20150308348A1 (en) * | 2013-05-22 | 2015-10-29 | United Technologies Corporation | Continuous detonation wave turbine engine |
RU2620736C1 (en) * | 2015-12-28 | 2017-05-29 | Открытое акционерное общество "Уфимское моторостроительное производственное объединение" ОАО "УМПО" | Method of organising working process in turbojet engine with continuously-detonating combustion chamber and device for its implementation |
US11493207B2 (en) | 2017-04-30 | 2022-11-08 | King Abdullah University Of Science And Technology | Auto-driven plasma actuator for transition from deflagration to detonation combustion regime and method |
RU184207U1 (en) * | 2018-02-28 | 2018-10-18 | Закрытое акционерное общество "Институт телекоммуникаций" | RESONANT AIR-REACTIVE ENGINE |
Also Published As
Publication number | Publication date |
---|---|
JP5764131B2 (en) | 2015-08-12 |
JP6055021B2 (en) | 2016-12-27 |
JP2015158356A (en) | 2015-09-03 |
US20120151898A1 (en) | 2012-06-21 |
RU2012115531A (en) | 2013-10-27 |
RU2537659C2 (en) | 2015-01-10 |
JP2013505399A (en) | 2013-02-14 |
US9046058B2 (en) | 2015-06-02 |
EP2480771B1 (en) | 2015-04-15 |
EP2480771A1 (en) | 2012-08-01 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US9046058B2 (en) | System and method of combustion for sustaining a continuous detonation wave with transient plasma | |
US6748735B2 (en) | Torch igniter | |
US4760820A (en) | Plasma jet ignition apparatus | |
US4471732A (en) | Plasma jet ignition apparatus | |
JP2009162478A (en) | Premixed, preswirled plasma-assisted pilot | |
KR20080092858A (en) | Electro-dynamic swirler, combustion apparatus and methods using the same | |
US8713908B2 (en) | Fuel injector arrangement having an igniter | |
RU2386846C2 (en) | Low-thrust rocket engine | |
RU2468240C1 (en) | Chamber of liquid-propellant rocket engine or gas generator with laser ignition device of fuel components, and its startup method | |
WO1992020913A1 (en) | Plasma ignition apparatus and method for enhanced combustion and flameholding in engine combustion chambers | |
RU2339840C2 (en) | Method of igniting fuel mixture in engine combustion chamber and device to this effect | |
US20050138933A1 (en) | Pulse detonation engine and method for initiating detonations | |
WO2008050006A3 (en) | Gas generator with primary and secondary chambers | |
RU2397355C2 (en) | Method of operating low-thrust rocket engine | |
RU2314456C1 (en) | Tubular-annular combustion chamber of gas-turbine engine | |
KR20200028324A (en) | Propulsion device of liquid propellant rocket engine | |
RU2642764C2 (en) | Solid-propellant rocket engine (versions) | |
RU125632U1 (en) | LOW ROCKET MOTOR CAMERA | |
RU2774001C1 (en) | Method for ignition and stabilization of combustion of fuel-air mixture by pulse optical quasi-stationary discharges and its implementation device | |
CA1245711A (en) | Plasma jet ignition apparatus | |
RU2103537C1 (en) | Gas generator | |
KR101729617B1 (en) | Subminiature premixed torch ignitor for a gas turbine engine | |
KR100465276B1 (en) | Ignitor for liquid fuel | |
SU548177A1 (en) | Arrangement for detonation application of coatings | |
WO2023275630A1 (en) | Pulsed detonation device for internal combustion engine and method |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
121 | Ep: the epo has been informed by wipo that ep was designated in this application |
Ref document number: 09838546 Country of ref document: EP Kind code of ref document: A1 |
|
WWE | Wipo information: entry into national phase |
Ref document number: 13392149 Country of ref document: US |
|
WWE | Wipo information: entry into national phase |
Ref document number: 2012530855 Country of ref document: JP |
|
NENP | Non-entry into the national phase |
Ref country code: DE |
|
WWE | Wipo information: entry into national phase |
Ref document number: 2009838546 Country of ref document: EP |
|
WWE | Wipo information: entry into national phase |
Ref document number: 2012115531 Country of ref document: RU |