CN109114593A - A kind of multi-step cascade combustion chamber for controlling detonation - Google Patents
A kind of multi-step cascade combustion chamber for controlling detonation Download PDFInfo
- Publication number
- CN109114593A CN109114593A CN201810828821.2A CN201810828821A CN109114593A CN 109114593 A CN109114593 A CN 109114593A CN 201810828821 A CN201810828821 A CN 201810828821A CN 109114593 A CN109114593 A CN 109114593A
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- China
- Prior art keywords
- combustion chamber
- detonation
- wall surface
- engine
- controlling
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Links
- 238000002485 combustion reaction Methods 0.000 title claims abstract description 41
- 238000005474 detonation Methods 0.000 title claims abstract description 35
- 230000006698 induction Effects 0.000 claims description 9
- 230000001939 inductive effect Effects 0.000 abstract 1
- 230000000087 stabilizing effect Effects 0.000 abstract 1
- 238000007906 compression Methods 0.000 description 3
- 230000008901 benefit Effects 0.000 description 2
- 230000000977 initiatory effect Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 239000000203 mixture Substances 0.000 description 2
- 210000001015 abdomen Anatomy 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 238000004904 shortening Methods 0.000 description 1
Classifications
-
- 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
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Combustion Methods Of Internal-Combustion Engines (AREA)
Abstract
本发明提供了一种用来控制爆轰的多台阶级联燃烧室，燃烧室应用于斜爆轰发动机，所述燃烧室的壁面沿周向设置多级向外侧延伸的斜坡台阶，台阶前侧为诱导壁面且后侧为爆轰稳定壁面。使用该燃烧室壁面结构将爆轰稳定在特定位置，可以达到控制发动机推力的目的。
The invention provides a multi-stage cascaded combustion chamber for controlling detonation. The combustion chamber is applied to an oblique detonation engine. The wall surface of the combustion chamber is provided with multi-stage slope steps extending to the outside along the circumferential direction. is the inducing wall and the rear side is the detonation stabilizing wall. Using the combustion chamber wall structure to stabilize the detonation at a specific position can achieve the purpose of controlling the thrust of the engine.
Description
Technical field
The present invention relates to a kind of Combustor Technologies, especially a kind of multi-step for controlling detonation cascades combustion chamber.
Background technique
Oblique detonation engine is the engine for being most hopeful that hypersonic vehicle is allowed to reach 7 times of velocities of sound or more
(Y.Zhang,J.Gong,T.Wang,Numerical study on initiation of oblique detonations
in hydrogen-air mixtures with various equivalence ratios,Aerospace Science
Technology49(2016)130-134).As hypersonic vehicle increasingly minimizes, small-sized hypersonic speed is developed
The engine of aircraft is extremely urgent.Detonation initiation position obtains extensive pass as the key factor for influencing combustion characteristics
Note.But the air-fuel for being concentrated mainly on air intake duct to the research of Combustion System in engine at present matches, the angle of combustion chamber wall surface
Degree variation.And traditional combustion chamber wall surface structure use smooth or flat construction, this class formation to steady detonation very not
Benefit.
Summary of the invention
The multi-step that the purpose of the present invention is to provide a kind of for controlling detonation cascades combustion chamber, uses the chamber wall
The purpose that can achieve control motor power in specific position is stablized in detonation by face structure.
Realize the technical solution of the object of the invention are as follows: a kind of multi-step cascade combustion chamber for controlling detonation, combustion chamber
Applied to oblique detonation engine, the slope step that the circumferentially arranged multistage of the wall surface of the combustion chamber extends outward, before step
Side is induction wall surface and rear side is that wall surface is stablized in detonation.
It is cascaded compared with prior art, the present invention having the advantage that by multi-step, the detonation that effectively shortens induction length
Detonation wave is stablized and is stablized on wall surface in the detonation after afterbody step by degree.
The invention will be further described with reference to the accompanying drawings of the specification.
Detailed description of the invention
Fig. 1 is engine axial section of the combustion chamber in lower section.
Fig. 2 is novel double step cascade combustion chamber wall surface.
Fig. 3 is engine transverse cross-sectional view of the combustion chamber in lower section.
The engine axial section of the combustion chamber Fig. 4 above.
Fig. 5 is the engine transverse cross-sectional view of combustion chamber above.
Fig. 6 is the axial section of the engine of cylindrical combustion chamber.
Fig. 7 is the radial cutaway view of the engine of cylindrical combustion chamber.
Fig. 8 is novel three-level step cascade combustion chamber wall surface.
Specific embodiment
A kind of multi-step cascade combustion chamber for controlling detonation, combustion chamber are applied to oblique detonation engine, and feature exists
On front side of, the slope step that the circumferentially arranged multistage of the wall surface of the combustion chamber extends outward, step for induction wall surface and after
Side is that wall surface is stablized in detonation.
Step structure can induce compression-expansion-compression process, the process can effectively shorten detonation wave induction length
Degree, and multi-step cascade can be realized the shortening of the induction length of higher limit, and detonation is stablized after afterbody step.
Embodiment as shown in connection with fig. 1, combustion chamber is in the lower section of engine main body, i.e. abdomen.Engine inlets are square
Shape structure, as shown in Fig. 3 horizontal section.Oblique detonation engine is by inlet end, combustion section, propelling nozzle section composition.Novel combustion
Burn locular wall face as shown in Fig. 2, the combustion chamber wall surface structure is made of five parts, first part is with supersonic speed incoming flow at centainly attacking
The induction wall surface at angle, second part are the steps connecting with induction wall surface, and Part III is the intermediate wall surface being connected with step, the
Four parts are two stage steps, and Part V is to be connected with two stage steps and stablize wall surface at the detonation of special angle with it.Induction
The length of wall surface, intermediate wall surface is determined by engine master-plan demand.Wall surface is induced, step, intermediate wall surface and detonation are steady
The angle determined between wall surface is determined by engine master-plan demand.Step can induce compression-expansion-compression process, more
Step cascade can induce multiple compression-expansion-compression processes, so that significantly smaller detonation induces length, so that detonation is steady
Detonation is scheduled on to stablize on wall surface.
Embodiment as shown in connection with fig. 4, combustion chamber is in the top of engine main body, i.e. top.Engine inlets are square
Shape structure, as shown in Fig. 5 horizontal section.In working principle and combustion chamber wall surface and Fig. 1.
Embodiment as shown in connection with fig. 6, combustion chamber are cylinder, and engine cylinder is also cylinder, see radial cutaway view-
Fig. 7, three-dimensional figure are shown in Fig. 8.It is the same in working principle Fig. 1.
Embodiment as shown in connection with fig. 8, wall surface are cascaded by three-level step, and engine wall surface can be cylinder can also
To be rectangle.
Claims (3)
1. a kind of multi-step for controlling detonation cascades combustion chamber, combustion chamber is applied to oblique detonation engine, which is characterized in that
The slope step that the circumferentially arranged multistage of the wall surface of the combustion chamber extends outward, step front side is induction wall surface and rear side is
Wall surface is stablized in detonation.
2. combustion chamber according to claim 1, which is characterized in that combustion chamber be located at oblique detonation engine top or under
Side, air intake duct cross section are rectangular configuration.
3. combustion chamber according to claim 1, which is characterized in that combustion chamber is logical for the circle with slope, the combustion chamber set
On oblique detonation engine.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810828821.2A CN109114593A (en) | 2018-07-25 | 2018-07-25 | A kind of multi-step cascade combustion chamber for controlling detonation |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810828821.2A CN109114593A (en) | 2018-07-25 | 2018-07-25 | A kind of multi-step cascade combustion chamber for controlling detonation |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109114593A true CN109114593A (en) | 2019-01-01 |
Family
ID=64863474
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810828821.2A Pending CN109114593A (en) | 2018-07-25 | 2018-07-25 | A kind of multi-step cascade combustion chamber for controlling detonation |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109114593A (en) |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3783616A (en) * | 1961-03-02 | 1974-01-08 | Garrett Corp | Control method for detonation combustion engines |
| GB2222635A (en) * | 1987-10-24 | 1990-03-14 | British Aerospace | A propulsion system for an aerospace vehicle |
| JP2003113740A (en) * | 2001-10-04 | 2003-04-18 | Mitsubishi Electric Corp | Missile |
| RU2285143C2 (en) * | 2004-12-10 | 2006-10-10 | Институт теоретической и прикладной механики СО РАН (ИТПМ СО РАН) | Method of organization of detonation combustion chamber of supersonic ramjet engine |
| WO2012011830A1 (en) * | 2010-07-19 | 2012-01-26 | Некоммерческое Партнерство "Центр Идг" | Device for transmitting a detonation |
| RU2012152753A (en) * | 2012-12-07 | 2014-06-20 | Федеральное государственное унитарное предприятие "Центральный аэрогидродинамический институт имени профессора Н.Е. Жуковского" (ФГУП "ЦАГИ") | METHOD FOR ORGANIZING A DETONATION COMBUSTION MODE IN THE COMBUSTION CHAMBER OF A HYPERSONIC DIRECT-AIR AIR-REACTIVE ENGINE |
| CN106968833A (en) * | 2017-03-29 | 2017-07-21 | 中国人民解放军国防科学技术大学 | A kind of supersonic speed detonation engine and its propulsion system |
| CN106968834A (en) * | 2017-03-29 | 2017-07-21 | 中国人民解放军国防科学技术大学 | A kind of supersonic speed detonation engine and its propulsion system |
-
2018
- 2018-07-25 CN CN201810828821.2A patent/CN109114593A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3783616A (en) * | 1961-03-02 | 1974-01-08 | Garrett Corp | Control method for detonation combustion engines |
| GB2222635A (en) * | 1987-10-24 | 1990-03-14 | British Aerospace | A propulsion system for an aerospace vehicle |
| JP2003113740A (en) * | 2001-10-04 | 2003-04-18 | Mitsubishi Electric Corp | Missile |
| RU2285143C2 (en) * | 2004-12-10 | 2006-10-10 | Институт теоретической и прикладной механики СО РАН (ИТПМ СО РАН) | Method of organization of detonation combustion chamber of supersonic ramjet engine |
| WO2012011830A1 (en) * | 2010-07-19 | 2012-01-26 | Некоммерческое Партнерство "Центр Идг" | Device for transmitting a detonation |
| RU2012152753A (en) * | 2012-12-07 | 2014-06-20 | Федеральное государственное унитарное предприятие "Центральный аэрогидродинамический институт имени профессора Н.Е. Жуковского" (ФГУП "ЦАГИ") | METHOD FOR ORGANIZING A DETONATION COMBUSTION MODE IN THE COMBUSTION CHAMBER OF A HYPERSONIC DIRECT-AIR AIR-REACTIVE ENGINE |
| CN106968833A (en) * | 2017-03-29 | 2017-07-21 | 中国人民解放军国防科学技术大学 | A kind of supersonic speed detonation engine and its propulsion system |
| CN106968834A (en) * | 2017-03-29 | 2017-07-21 | 中国人民解放军国防科学技术大学 | A kind of supersonic speed detonation engine and its propulsion system |
Non-Patent Citations (1)
| Title |
|---|
| 范孝华: "《壁面条件对爆震波起爆以及传播过程影响机理的研究》", 《中国优秀硕士学位论文全文数据库 工程科技Ⅱ辑》 * |
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| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20190101 |
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