RU2013150684A - METHOD FOR ORGANIZING IGNITION AND COMBUSTION OF FUEL IN A HYPERSONIC DIRECT FLOW AIR-REACTIVE ENGINE (SCREW) - Google Patents
METHOD FOR ORGANIZING IGNITION AND COMBUSTION OF FUEL IN A HYPERSONIC DIRECT FLOW AIR-REACTIVE ENGINE (SCREW) Download PDFInfo
- Publication number
- RU2013150684A RU2013150684A RU2013150684/06A RU2013150684A RU2013150684A RU 2013150684 A RU2013150684 A RU 2013150684A RU 2013150684/06 A RU2013150684/06 A RU 2013150684/06A RU 2013150684 A RU2013150684 A RU 2013150684A RU 2013150684 A RU2013150684 A RU 2013150684A
- Authority
- RU
- Russia
- Prior art keywords
- combustion
- fuel
- ignition
- organizing
- supplied
- Prior art date
Links
Landscapes
- Ignition Installations For Internal Combustion Engines (AREA)
- Combustion Methods Of Internal-Combustion Engines (AREA)
- Electrical Control Of Air Or Fuel Supplied To Internal-Combustion Engine (AREA)
Abstract
1. Способ организации воспламенения и горения топлива в гиперзвуковом прямоточном воздушно-реактивном двигателе (ГПВРД) высокоскоростного летательного аппарата, содержащего камеру сгорания, куда через систему пилонов, обтекаемых кислородом, например, в составе воздуха подают горючее со сверхзвуковой скоростью и воспламеняют топливовоздушную смесь, инициируя цепной механизм горения и энерговыделение в проточном тракте камеры, отличающийся тем, что на границе раздела воздуха и горючего, по меньшей мере, на выходе одного из пилонов, формируют струю холодной кислородной плазмы определенного поперечного размера d, воздействуя на кислород электрическим разрядом с определенной величиной удельного энерговклада Eи приведенной напряженностью электрического поля E/N, где E - напряженность электрического поля, a N - числовая плотность молекул газа.2. Способ организации воспламенения и горения топлива в ГПВРД по п.1, отличающийся тем, что применяют оптимальные значения поперечного размера d струи холодной кислородной плазмы, параметра E/N и длины зоны горения в проточном тракте камеры сгорания, обеспечивающих наименьшие длины зон воспламенения и энерговыделения, а также максимальную полноту сгорания и максимальную эффективность использования энергии, подведенной к газу в разряде при заданной E.3. Способ организации воспламенения и горения топлива в ГПВРД по п.1 или 2, отличающийся тем, что при подаче горючего в виде водорода толщина d струи холодной кислородной плазмы составляет не менее 0.5% от поперечного размера камеры сгорания, а значение приведенной напряженности электрического поля находятся в диапазоне E/N=5-10·10В·с1. A method of organizing ignition and combustion of fuel in a hypersonic ramjet engine (SCJP) of a high-speed aircraft containing a combustion chamber, where, through a system of pylons streamlined with oxygen, for example, air is supplied with supersonic speed and ignites the air-fuel mixture, initiating chain combustion mechanism and energy release in the flow path of the chamber, characterized in that at the interface between air and fuel, at least at the outlet of one of the pylons, forms ruyut stream of cold oxygen plasma certain transverse dimension d, the oxygen acting on an electric discharge at a certain value of the specific energy E and the reduced electric field E / N, wherein E - electric field strength, a N - the number density of molecules gaza.2. The method of organizing ignition and combustion of fuel in the scramjet according to claim 1, characterized in that the optimum values of the transverse dimension d of the jet of cold oxygen plasma, the E / N parameter and the length of the combustion zone in the flow path of the combustion chamber are used, which provide the smallest lengths of the ignition and energy zones, as well as the maximum completeness of combustion and the maximum efficiency of the use of energy supplied to the gas in the discharge at a given E.3. The method of organizing ignition and combustion of fuel in the scramjet according to claim 1 or 2, characterized in that when the fuel is supplied in the form of hydrogen, the thickness d of the cold oxygen plasma jet is at least 0.5% of the transverse size of the combustion chamber, and the reduced electric field strength is range E / N = 5-10 · 10V · s
Claims (4)
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
RU2013150684/06A RU2550209C1 (en) | 2013-11-14 | 2013-11-14 | Method of ignition and combustion of fuel in athodyd |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
RU2013150684/06A RU2550209C1 (en) | 2013-11-14 | 2013-11-14 | Method of ignition and combustion of fuel in athodyd |
Publications (2)
Publication Number | Publication Date |
---|---|
RU2550209C1 RU2550209C1 (en) | 2015-05-10 |
RU2013150684A true RU2013150684A (en) | 2015-05-20 |
Family
ID=53283859
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
RU2013150684/06A RU2550209C1 (en) | 2013-11-14 | 2013-11-14 | Method of ignition and combustion of fuel in athodyd |
Country Status (1)
Country | Link |
---|---|
RU (1) | RU2550209C1 (en) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
RU2604975C2 (en) * | 2015-04-20 | 2016-12-20 | Сергей Николаевич Чувашев | Hypersonic aircraft with ramjet with increased flight and technical characteristics |
US10794331B2 (en) | 2017-07-31 | 2020-10-06 | The Boeing Company | Scramjets and associated aircraft and methods |
Family Cites Families (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3430446A (en) * | 1964-04-20 | 1969-03-04 | Us Navy | External burning ramjet engine |
US5085048A (en) * | 1990-02-28 | 1992-02-04 | General Electric Company | Scramjet including integrated inlet and combustor |
RU2265158C1 (en) * | 2004-05-17 | 2005-11-27 | Монич Антон Евгеньевич | Mode of incineration of hydrocarbon fuel and an arrangement for realization of this mode |
RU2333381C2 (en) * | 2005-11-03 | 2008-09-10 | Нек Лаб Холдинг Инк. | Method of initation ignition, intensifying combustion or reforming of fuel-air and fuel-oxygen mixes |
RU2323237C1 (en) * | 2006-09-28 | 2008-04-27 | Государственное учреждение Институт технической химии Уральского отделения Российской академии наук (ИТХ УрО РАН) | Frost-resistant polyurethane composition for articles produced by casting |
RU2446305C2 (en) * | 2010-06-28 | 2012-03-27 | Институт теоретической и прикладной механики им. С.А. Христиановича Сибирского отделения Российской академии наук (ИТПМ СО РАН) | Supersonic ramjet engine with pulsating combustion and method of its operation |
-
2013
- 2013-11-14 RU RU2013150684/06A patent/RU2550209C1/en active
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
RU2604975C2 (en) * | 2015-04-20 | 2016-12-20 | Сергей Николаевич Чувашев | Hypersonic aircraft with ramjet with increased flight and technical characteristics |
US10794331B2 (en) | 2017-07-31 | 2020-10-06 | The Boeing Company | Scramjets and associated aircraft and methods |
Also Published As
Publication number | Publication date |
---|---|
RU2550209C1 (en) | 2015-05-10 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
Wang et al. | Induction for multiple rotating detonation waves in the hydrogen–oxygen mixture with tangential flow | |
CN104330519A (en) | Particle airflow suspension laser ignition experiment device | |
CN103343983B (en) | Supersonic-speed stable combustion method based on strong magnetic field stable electric arc | |
EP3438437B1 (en) | Scramjets and associated aircraft and methods | |
RU2013119486A (en) | COMBUSTION CHAMBER INJECTOR, GAS TURBINE, METHOD INCLUDING AIR AND FUEL MIXING, AND METHOD INCLUDING AT LEAST ONE CHANNEL | |
RU2013150684A (en) | METHOD FOR ORGANIZING IGNITION AND COMBUSTION OF FUEL IN A HYPERSONIC DIRECT FLOW AIR-REACTIVE ENGINE (SCREW) | |
Korytchenko et al. | Experimental research into the influence of two-spark ignition on the deflagration to detonation transition process in a detonation tube | |
RU2010145251A (en) | METHOD FOR COMBUSTION ORGANIZATION IN A HYPERSONIC REDUCED AIR-REACTIVE ENGINE AND A HYPERSONIC REDUCED AIR-REACTIVE ENGINE | |
RU2014101385A (en) | HYBRID ROCKET AND RECTANOUS AIR-REACTIVE AEROSPACE ENGINE | |
RU2013129579A (en) | COMBUSTION CAMERA INJECTOR, GAS TURBINE AND METHOD INCLUDING AIR AND FUEL MIXING | |
RU2012152753A (en) | METHOD FOR ORGANIZING A DETONATION COMBUSTION MODE IN THE COMBUSTION CHAMBER OF A HYPERSONIC DIRECT-AIR AIR-REACTIVE ENGINE | |
RU2014106079A (en) | METHOD FOR ORGANIZING FUEL BURNING AND DETONATION-DEFLAGRATION PULSING RECTANGULAR AIR-REACTIVE ENGINE | |
Chen et al. | Influences of separate injectors on rotating detonation engines | |
RU2595004C9 (en) | Method for detonation combustion of fuel mixtures and device for its implementation | |
RU2010126476A (en) | SUPERSONIC RECTANGULAR AIR-REACTIVE ENGINE WITH PULSE-BURNING COMBUSTION MODE (SPRDR with PRG) AND METHOD OF ITS OPERATION | |
RU2490491C1 (en) | Device for pulse ignition of combustible mixture | |
RU2568854C1 (en) | Method of formation of thrust of engine with central body and engine for its implementation | |
RU2511921C1 (en) | Hypersonic propulsive jet engine, and combustion arrangement method | |
Zhang et al. | Numerical studies of multi-cycle acetylene-air detonation induced by shock focusing | |
Dhatchanamoorthy et al. | Study and performance analysis of gas turbine combustion chamber and improving combustion efficiency by using ceramic composite material coating | |
Suchomel et al. | Perspectives on cataloging plasma technologies applied to aeronautical sciences | |
Firsov et al. | Advanced Ignition in Supersonic Airflow by Tunable Plasma System | |
Crismaru et al. | The influence of the flame stabilization air intake holes diameter on the no production in an industrial gas turbine | |
RU125632U1 (en) | LOW ROCKET MOTOR CAMERA | |
RU2447368C1 (en) | Method for ignition of fuel mix flow and device for its implementation (versions) |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
PC43 | Official registration of the transfer of the exclusive right without contract for inventions |
Effective date: 20210804 |