CN109140497A - A kind of combustion chamber for controlling oblique detonation and starting interior detonation point initiation - Google Patents
A kind of combustion chamber for controlling oblique detonation and starting interior detonation point initiation Download PDFInfo
- Publication number
- CN109140497A CN109140497A CN201810827880.8A CN201810827880A CN109140497A CN 109140497 A CN109140497 A CN 109140497A CN 201810827880 A CN201810827880 A CN 201810827880A CN 109140497 A CN109140497 A CN 109140497A
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- CN
- China
- Prior art keywords
- detonation
- combustion chamber
- wall surface
- engine
- oblique
- Prior art date
- Legal status (The legal status 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 status listed.)
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Classifications
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- 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
- F23R3/002—Wall structures
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- 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
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
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- 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
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- 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
The present invention provides a kind of combustion chamber for controlling oblique detonation and starting interior detonation point initiation, combustion chamber is applied to oblique detonation engine, the circumferentially arranged slope extended outward of the wall surface of the combustion chamber, and step front side is induction wall surface and rear side is that wall surface is stablized in detonation.Detonation is stablized to the purpose that can achieve control motor power in specific position using the combustion chamber wall surface structure.
Description
Technical field
The present invention relates to a kind of Combustor Technologies, especially a kind of burning for controlling oblique detonation and starting interior detonation point initiation
Room.
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
inhydrogen-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 purpose of the present invention is to provide a kind of combustion chambers for controlling oblique detonation and starting interior detonation point initiation, use the combustion
It burns room wall structure to stablize detonation in specific position, achievees the purpose that control motor power.
Realize the technical solution of the object of the invention are as follows: a kind of combustion chamber of movable step control detonation, combustion chamber is applied to
Oblique detonation engine, which is characterized in that the circumferentially arranged slope extended outward of the wall surface of the combustion chamber, step front side are
It induces wall surface and rear side is that wall surface is stablized in detonation.
The sliding on wall surface is stablized in detonation by step compared with prior art, the present invention having the advantage that, is realized
Any control of detonation position, to control the combustion process in detonation engine.
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 schematic diagram before and after step movement.
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 cylindrical combustion chamber wall surface 3-D view.
Specific embodiment
A kind of combustion chamber for controlling oblique detonation and starting interior detonation point initiation, combustion chamber are applied to oblique detonation engine, institute
The circumferentially arranged slope step extended outward of wall surface of combustion chamber is stated, step front side is induction wall surface and rear side is that detonation is steady
Determine wall surface, and the slope is along planar slide where combustion chamber wall surface.It is on front side of step on the left of step in Fig. 1.
The angle of wall surface and step is induced, the angle that wall surface is stablized in step and detonation is true according to real engine master-plan
It is fixed.
Wall surface length is induced, length of bench is determined according to real engine master-plan.
Step has Aircraft Conceptual Design demand and engine master-plan along the mode that wall sliding is stablized in detonation
Demand determines.
Supersonic speed incoming flow forms first shock wave on induction wall surface, this shock wave has carried out first to supersonic speed incoming flow
Second compression, after step, incoming flow expansion accelerates, and then stablizes in detonation wave and forms second shock wave on wall surface, by this
After one compression-expansion of sample-recompression process, the temperature after second shock wave is obviously improved, so as to shorten detonation induction time,
Detonation wave is stablized after 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
Locular wall face is burnt as shown in Fig. 2, increasing step structure on original smooth wall surface.New combustion chamber wall surface is by induction wall surface, step,
Detonation wave stablizes wall surface composition.The length of stepped locations L1, i.e. induction wall surface are arranged according to actual thrust demand.Step depth H
It is determined according to actual thrust demand by experiment effect.The angle and step and detonation of step and induction wall surface stablize the folder of wall surface
Angle is determined according to real engine master-plan.
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.
Claims (3)
1. a kind of combustion chamber for controlling oblique detonation and starting interior detonation point initiation, which is characterized in that the wall surface edge of the combustion chamber
The slope step extended outward is circumferentially set, and step front side is induction wall surface and rear side is that 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 |
|---|---|---|---|
| CN201810827880.8A CN109140497A (en) | 2018-07-25 | 2018-07-25 | A kind of combustion chamber for controlling oblique detonation and starting interior detonation point initiation |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810827880.8A CN109140497A (en) | 2018-07-25 | 2018-07-25 | A kind of combustion chamber for controlling oblique detonation and starting interior detonation point initiation |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109140497A true CN109140497A (en) | 2019-01-04 |
Family
ID=64799000
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810827880.8A Pending CN109140497A (en) | 2018-07-25 | 2018-07-25 | A kind of combustion chamber for controlling oblique detonation and starting interior detonation point initiation |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109140497A (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3783616A (en) * | 1961-03-02 | 1974-01-08 | Garrett Corp | Control method for detonation combustion engines |
| GB2222635B (en) * | 1987-10-24 | 1992-05-27 | British Aerospace | Propulsion units for aerospace vehicles |
| JP2003113740A (en) * | 2001-10-04 | 2003-04-18 | Mitsubishi Electric Corp | Missile |
| US6880342B1 (en) * | 2003-07-16 | 2005-04-19 | The United States Of America As Represented By The Secretary Of The Air Force | Structure and method for controlling inlet shock position of a hypersonic vehicle |
| 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 CN201810827880.8A patent/CN109140497A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3783616A (en) * | 1961-03-02 | 1974-01-08 | Garrett Corp | Control method for detonation combustion engines |
| GB2222635B (en) * | 1987-10-24 | 1992-05-27 | British Aerospace | Propulsion units for aerospace vehicles |
| JP2003113740A (en) * | 2001-10-04 | 2003-04-18 | Mitsubishi Electric Corp | Missile |
| US6880342B1 (en) * | 2003-07-16 | 2005-04-19 | The United States Of America As Represented By The Secretary Of The Air Force | Structure and method for controlling inlet shock position of a hypersonic vehicle |
| 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 |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20190104 |