RU2012152753A - METHOD FOR ORGANIZING A DETONATION COMBUSTION MODE IN THE COMBUSTION CHAMBER OF A HYPERSONIC DIRECT-AIR AIR-REACTIVE ENGINE - Google Patents
METHOD FOR ORGANIZING A DETONATION COMBUSTION MODE IN THE COMBUSTION CHAMBER OF A HYPERSONIC DIRECT-AIR AIR-REACTIVE ENGINE Download PDFInfo
- Publication number
- RU2012152753A RU2012152753A RU2012152753/06A RU2012152753A RU2012152753A RU 2012152753 A RU2012152753 A RU 2012152753A RU 2012152753/06 A RU2012152753/06 A RU 2012152753/06A RU 2012152753 A RU2012152753 A RU 2012152753A RU 2012152753 A RU2012152753 A RU 2012152753A
- Authority
- RU
- Russia
- Prior art keywords
- combustion chamber
- combustion
- air
- detonation
- fuel
- Prior art date
Links
- 238000002485 combustion reaction Methods 0.000 title claims abstract 24
- 238000005474 detonation Methods 0.000 title claims abstract 9
- 238000000034 method Methods 0.000 title claims abstract 3
- 239000000446 fuel Substances 0.000 claims abstract 12
- 239000000203 mixture Substances 0.000 claims abstract 8
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims abstract 2
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 claims abstract 2
- 239000002041 carbon nanotube Substances 0.000 claims abstract 2
- 229910021393 carbon nanotube Inorganic materials 0.000 claims abstract 2
- 230000005684 electric field Effects 0.000 claims abstract 2
- 229910052739 hydrogen Inorganic materials 0.000 claims abstract 2
- 239000001257 hydrogen Substances 0.000 claims abstract 2
- 230000010349 pulsation Effects 0.000 claims abstract 2
- 230000035939 shock Effects 0.000 claims abstract 2
- 239000000126 substance Substances 0.000 claims abstract 2
Landscapes
- Combustion Methods Of Internal-Combustion Engines (AREA)
Abstract
Способ организации детонационного режима горения в камере сгорания гиперзвукового прямоточного воздушно-реактивного двигателя, включающий сжатие воздуха в системе внешних и внутренних скачков уплотнения, возникающих на фиксированных и регулируемых элементах фюзеляжа и силовой установки, подачу топлива за внешней системой скачков перед камерой сгорания, формирование на ее входе детонационной волны, детонационное горение топливовоздушной смеси в камере сгорания, регулирование положения детонационной волны в камере сгорания в зависимости от числа Маха потока на входе в камеру сгорания посредством изменения геометрических параметров камеры сгорания и химического состава поступающей топливовоздушной смеси и последующее расширение продуктов горения в сопле, отличающийся тем, что топливовоздушную смесь создают на основе нанодисперсного топлива, содержащего углеродные нанотрубки с капсулированным в них водородом, которое вводят перед камерой сгорания через отверстия игольчатой топливной форсунки навстречу набегающему потоку, и генерируют в зоне горения пульсирующее электрическое поле напряженностью более 20 В/см.A method of organizing a detonation mode of combustion in a combustion chamber of a hypersonic ramjet engine, comprising compressing air in a system of external and internal shock waves occurring on fixed and adjustable elements of the fuselage and power plant, supplying fuel behind an external jump system in front of the combustion chamber, forming detonation wave input, detonation combustion of the air-fuel mixture in the combustion chamber, regulation of the position of the detonation wave in the combustion chamber depending of the Mach number of the flow at the entrance to the combustion chamber by changing the geometric parameters of the combustion chamber and the chemical composition of the incoming air-fuel mixture and the subsequent expansion of the combustion products in the nozzle, characterized in that the air-fuel mixture is created on the basis of nanodispersed fuel containing carbon nanotubes with hydrogen encapsulated in them which is introduced in front of the combustion chamber through the openings of the needle fuel nozzle towards the incoming flow, and a pulsation is generated in the combustion zone The present electric field intensity of 20 V / cm.
Claims (1)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| RU2012152753/06A RU2520784C1 (en) | 2012-12-07 | 2012-12-07 | Setting of detonation combustion in combustion chamber of hypersonic ramjet |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| RU2012152753/06A RU2520784C1 (en) | 2012-12-07 | 2012-12-07 | Setting of detonation combustion in combustion chamber of hypersonic ramjet |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| RU2012152753A true RU2012152753A (en) | 2014-06-20 |
| RU2520784C1 RU2520784C1 (en) | 2014-06-27 |
Family
ID=51213427
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| RU2012152753/06A RU2520784C1 (en) | 2012-12-07 | 2012-12-07 | Setting of detonation combustion in combustion chamber of hypersonic ramjet |
Country Status (1)
| Country | Link |
|---|---|
| RU (1) | RU2520784C1 (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109114591A (en) * | 2018-07-25 | 2019-01-01 | 南京理工大学 | It is a kind of to change the combustion chamber for realizing detonation control by wall angle |
| CN109114593A (en) * | 2018-07-25 | 2019-01-01 | 南京理工大学 | A kind of multi-step cascade combustion chamber for controlling detonation |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108488004B (en) * | 2018-01-25 | 2021-02-26 | 南京航空航天大学 | A stationary detonation engine based on variable wedge angle |
| CN109114590A (en) * | 2018-07-25 | 2019-01-01 | 南京理工大学 | A kind of combustion chamber of movable step control detonation |
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 |
| FR2149313B1 (en) * | 1971-08-19 | 1976-06-25 | Snecma | |
| RU2028488C1 (en) * | 1988-06-30 | 1995-02-09 | Блинчевский Мнахем Яковлевич | Ramjet engine |
| EP0370209A1 (en) * | 1988-10-06 | 1990-05-30 | The Boeing Company | Engine for low-speed to hypersonic vehicles |
| US5085048A (en) * | 1990-02-28 | 1992-02-04 | General Electric Company | Scramjet including integrated inlet and combustor |
| RU2262000C2 (en) * | 2003-10-20 | 2005-10-10 | Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения им. П.И. Баранова" | Hypersonic ramjet engine and method of organization of combustion |
-
2012
- 2012-12-07 RU RU2012152753/06A patent/RU2520784C1/en active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109114591A (en) * | 2018-07-25 | 2019-01-01 | 南京理工大学 | It is a kind of to change the combustion chamber for realizing detonation control by wall angle |
| CN109114593A (en) * | 2018-07-25 | 2019-01-01 | 南京理工大学 | A kind of multi-step cascade combustion chamber for controlling detonation |
Also Published As
| Publication number | Publication date |
|---|---|
| RU2520784C1 (en) | 2014-06-27 |
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