CN106870203A - The scramjet engine of fluidized powder propellant - Google Patents
The scramjet engine of fluidized powder propellant Download PDFInfo
- Publication number
- CN106870203A CN106870203A CN201710201379.6A CN201710201379A CN106870203A CN 106870203 A CN106870203 A CN 106870203A CN 201710201379 A CN201710201379 A CN 201710201379A CN 106870203 A CN106870203 A CN 106870203A
- Authority
- CN
- China
- Prior art keywords
- orifice plate
- propellant
- air inlet
- center body
- jet
- 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.)
- Pending
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Classifications
-
- 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
- F02K7/10—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 characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
- F02K7/105—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 characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines using a solid fuel
-
- 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
- F02K9/70—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using semi- solid or pulverulent propellants
Abstract
The present invention relates to a kind of scramjet engine of fluidized powder propellant, including shell and air inlet passage center body, the inner chamber of shell parcel is divided into air intake duct, combustion chamber and the part of jet pipe three；Embedding propellant tank in air inlet passage center body, perforate forms convergent passage on air inlet passage center body, and with propellant tank be connected air intake duct by convergent passage；Air inlet passage center body end convergent passage is provided with premixer as the jet of powdered solid propellant between propellant tank and jet, spark plug is circumferentially arranged on jet；Propellant tank end is equipped with flow regulator.The present invention is simple and compact for structure, and lighter weight, reliability is high, overcoming solid propellant can not repeatedly start and the nonadjustable difficulty of flow, while making full use of Incoming gas, improve the density and sweay of propellant, engine/motor specific impulse is improve, efficiency of combustion is improve.
Description
Technical field
Start the present invention relates to a kind of scramjet engine, more particularly to a kind of ultra-combustion ramjet of fluidized powder propellant
Machine.
Background technology
Turn into the new battlefield in modern war along with the development near space of science and technology.Near space generally refer to away from
The spatial domain of 20~100km of ground, between aircraft highest flying height and the minimum high speed of space orbit aircraft, not only has
Comparatively safe working environment, additionally it is possible to provide, more accurate information more more than satellite with relatively low cost.When flying height expands
When opening up near space, turbojet and sub- burning ramjet all encounter serious bottleneck.Therefore, ultra-combustion ramjet
Engine fuel specific impulse is far above existing turbojet and compression ignition punching engine, can realize flight speed higher
Degree and flying height, while reducing space transoportation cost, it is adaptable to hypersonic cruise missile, Hypersonic Aircraft and empty day
The course of new aircraft such as aircraft.
Existing development, scramjet engine on probation belong to airbreathing propulsion system, self-contained fuel rich propellant.Come
Stream air enters combustion chamber by air intake duct, and supersonic speed chemically reacts to flow with propellant in combustion chamber, the height of generation
Fast gas ejects generation thrust from jet pipe.Propellant type by using can be divided into solid fuel scramjet engine and
Two kinds of liquid fuel scramjet engine.
The shortcoming of solid propellant scramjet engine is uncontrollable flow, it is impossible to repeatedly start/flame-out.Liquid is advanced
Agent scramjet engine security is relatively low, and propellant bulk density is small, complex structure.Simultaneously current ultra-combustion ramjet starts
It is low that machine all suffers from efficiency of combustion, the problems such as treatment and inconvenient storage.
The content of the invention
The technical problem to be solved in the present invention is to provide a kind of scramjet engine of fluidized powder propellant, to solve
Overcoming solid propellant can not repeatedly start and the nonadjustable difficulty of flow, while making full use of Incoming gas, raising is started
The problem of machine specific impulse.
It is the technical problem for solving to exist, the technical solution adopted by the present invention is：A kind of super burn of fluidized powder propellant
Punching engine, including shell and air inlet passage center body, the inner chamber of described shell parcel are divided into air intake duct, combustion chamber and jet pipe
Three parts, the inner chamber that shell parcel air inlet passage center body is formed is air intake duct, what air flue centerbody end to shell afterbody was wrapped up
Inner chamber is combustion chamber, and the outlet of shell afterbody is jet pipe；Embedding propellant tank, propellant tank in described air inlet passage center body
The powdered solid propellant of interior filling, perforate forms convergent passage on air inlet passage center body, convergent passage be located at air intake duct every
From section original position, with propellant tank be connected air intake duct by convergent passage, and the partial air in air intake duct is directly introduced pushing away
Enter in agent tank；Air inlet passage center body end convergent passage as powdered solid propellant jet, propellant tank
Premixer is provided between jet, spark plug is circumferentially arranged on jet；Described propellant tank end is equipped with stream
Quantity regulating device, the Flow-rate adjustment of the powdered solid propellant for fluidizing.
Flow regulator of the invention can be using the flow of the existing powdered solid propellants such as flow control valve
Adjusting means, one kind disclosed by the invention uses circular plate type flow regulator, described circular plate type using flow regulator
Flow regulator is constituted by fixing orifice plate and rotatable orifice plate, and circular stomata of the same size is evenly arranged on fixed orifice plate,
Edge is disposed with multiple fixing hole board grooves, for being connected with rotatable orifice plate；It is radially arranged on rotatable orifice plate to have one week
Crescent air drain, the radial position of each crescent air drain is corresponding with the radial position of corresponding circular stomata, rotatable hole
The edges of boards edge raised draw-in grooves of multiple rotatable orifice plates with projection that are disposed with corresponding to fixing hole board groove correspondence position are used for and solid
Determine orifice plate to be connected, rotatable orifice plate is arranged in the fixing hole board groove of fixed orifice plate by rotatable orifice plate projection draw-in groove, can
Rotate orifice plate to be arranged on fixed orifice plate in draw-in groove form, rotatable orifice plate simultaneously passes through to rotate the crescent of the rotatable orifice plate of regulation
The aperture area of air drain, so as to adjust the flow of powdered solid propellant.
Beneficial effect：It is the same that fluidized powder scramjet engine of the invention can provide same liquid propellant engine
The ability that flow is controlled and repeatedly started, overcoming solid propellant can not repeatedly start and the nonadjustable difficulty of flow,
There is the security of solid propellant engine simultaneously.Fluidized powder propellant will not run into Low Temperature Problems, and this is even best consolidating
The problem that body and non-frozen liquid propellant engine can all run into.No matter rushed with liquid propellant or solid propellant super burn
Hydraulic motor is compared, fluidized powder propellant due to impact zone be easier dispersion, therefore can reach more fully mixing and
Burning.Make it be easier to process compared to other scramjet engines due to the stored condition of the powder propellant, store
And packaging.
The present invention it is simple and compact for structure, lighter weight, reliability is high, overcome solid propellant can not repeatedly start and
The nonadjustable difficulty of flow, while making full use of Incoming gas, improves the density and sweay of propellant, improves engine
Specific impulse, improves efficiency of combustion.The present invention can be as various hypersonic vehicle power propulsion systems.
Brief description of the drawings
Fig. 1 is the appearance schematic diagram of fluidized powder propellant scramjet engine of the present invention；
Fig. 2 is the inner structure schematic diagram of fluidized powder propellant scramjet engine of the present invention；
Fig. 3 is the fixed orifice plate schematic diagram of fluidized powder propellant scramjet engine of the present invention；
Fig. 4 is the rotatable orifice plate schematic diagram of fluidized powder propellant scramjet engine of the present invention；
Each numeral is expressed as follows respectively as shown in the figure：1. shell；2. air inlet passage center body；3. propellant tank；4. spark plug；5.
Air intake duct；6. combustion chamber；7. jet pipe；8. convergent passage；9. jet；10. premixer；11. fix orifice plate；12. rotatable holes
Plate；13. circular stomatas；14. fixing hole board grooves；15. crescent air drains；16. rotatable orifice plate projection draw-in grooves.
Specific embodiment
The present invention is described further with reference to the accompanying drawings and examples.
As shown in Figure 1-2, a kind of fluidized powder propellant scramjet engine, including shell 1, air inlet passage center body 2,
Propellant tank 3 and spark plug 4.The inner chamber of the parcel of shell 1 is divided into three parts：Air intake duct 5, combustion chamber 6 and jet pipe 7, propellant
Tank 3 is embedded in air inlet passage center body 2, the superfine powdered solid propellant of filling in propellant tank 3.In air intake duct
On centerbody 2 perforate formed convergent passage 8, convergent passage 8 be located at the distance piece original position of air intake duct 5, and with convergent passage 8 with
Propellant tank 3 is connected, and the partial air in air intake duct 5 directly is introduced into propellant tank 3, and the end of air inlet passage center body 2 is received
Jet 9 of the passage as fuel is held back, premixer 10 is provided between propellant tank 3 and jet 9, along ring on jet 9
To arrangement spark plug 4.The end of propellant tank 3 is equipped with fixed orifice plate 11 and rotatable orifice plate 12, advances the powder of fluidisation
Agent flux is adjustable.
As shown in Figure 3-4, the end of propellant tank 3 is equipped with fixed orifice plate 11 and rotatable orifice plate 12, makes the powder of fluidisation
Last propellant flow rate is adjustable.Circular stomata 13 of the same size is evenly arranged on fixed orifice plate 11,6 fixed orifice plates are arranged at edge
Draw-in groove 14 is used to be connected with rotatable orifice plate 12.Radially arranged one week crescent air drain 15, edge cloth on rotatable orifice plate 12
Put 6 is used to be connected with fixed orifice plate 11 with raised rotatable orifice plate projection draw-in groove 16.Rotatable orifice plate 12 is in draw-in groove form
It is rotational angle unit with 60 ゜ on fixed orifice plate 11.The variable more flow control valve of circular plate type flow regulator.
During specific works, incoming air enters air intake duct, into air intake duct a gas part be directly entered combustion chamber with
There is chemical reaction and produce thrust in propellant, another part enters propellant tank by the convergent passage on centerbody.Extruding
After gas enters propellant tank, the air pressure in increase tank makes powder propellant suspend, by the continuous air for spraying into
Drive pulverized fuel that tank is flowed out as liquid, blowing loophole sprays.By rotating the rotatable orifice plate of tank end, regulation
The aperture area of orifice plate, so as to adjust the flow of powder propellant.Powder propellant in premixer with air-flow expansion after
Suspended motion is held in continuation of insurance, more uniform with air blending, and the spark plug and the air in combustion chamber by centerbody end occur
Combustion chamber is flowed through in violent chemical reaction, combustion gas, is sprayed by jet pipe and produces thrust.
As a result the present invention proves feasible through overtesting.
Claims (2)
1. a kind of scramjet engine of fluidized powder propellant, including shell（1）With air inlet passage center body（2）, its feature
It is：
Described shell（1）The inner chamber of parcel is divided into air intake duct（5）, combustion chamber（6）And jet pipe（7）Three parts, shell（1）Parcel
Air inlet passage center body（2）The inner chamber of formation is air intake duct（5）, air flue centerbody（2）End is to shell（1）The inner chamber of afterbody parcel
It is combustion chamber（6）, shell（1）The outlet of afterbody is jet pipe（7）；
Described air inlet passage center body（2）Embedded propellant tank（3）, propellant tank（3）The powdered solid of interior filling is pushed away
Enter agent, air inlet passage center body（2）Upper perforate forms convergent passage（8）, convergent passage（8）Positioned at air intake duct（5）Distance piece starting
Position, convergent passage（8）By air intake duct（5）With propellant tank（3）It is connected, directly by air intake duct（5）Interior partial air draws
In entering propellant tank（3）；Air inlet passage center body（2）End convergent passage as powdered solid propellant jet
（9）, propellant tank（3）With jet（9）Between be provided with premixer（10）, in jet（9）On circumferentially arrange spark plug
（4）；
Described propellant tank（3）End is equipped with flow regulator, the stream of the powdered solid propellant for fluidizing
Amount regulation.
2. scramjet engine according to claim 1, it is characterised in that：Described flow regulator uses plectane
Formula flow regulator, circular plate type flow regulator is by fixing orifice plate（11）And rotatable orifice plate（12）Composition, fixed orifice plate
（11）On be evenly arranged circular stomata of the same size（13）, edge is disposed with multiple fixing hole board grooves（14）, for can
Rotate orifice plate（12）It is connected；Rotatable orifice plate（12）It is above radially arranged to have one week crescent air drain（15）, each crescent gas
Groove（15）Radial position and corresponding circular stomata（13）Radial position it is corresponding, rotatable orifice plate（12）Edge and fixation
Orifice plate draw-in groove（14）Correspondence position is accordingly disposed with multiple with raised rotatable orifice plate projection draw-in groove（16）For and fixing hole
Plate（11）It is connected, rotatable orifice plate（12）By rotatable orifice plate projection draw-in groove（16）Installed in fixed orifice plate（11）Fixing hole
Board groove（14）In, rotatable orifice plate（12）Fixed orifice plate is arranged in draw-in groove form（11）On, rotatable orifice plate（12）And lead to
Cross the rotation rotatable orifice plate of regulation（12）Crescent air drain（15）Aperture area, so as to adjust powdered solid propellant
Flow.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710201379.6A CN106870203A (en) | 2017-03-30 | 2017-03-30 | The scramjet engine of fluidized powder propellant |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710201379.6A CN106870203A (en) | 2017-03-30 | 2017-03-30 | The scramjet engine of fluidized powder propellant |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106870203A true CN106870203A (en) | 2017-06-20 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710201379.6A Pending CN106870203A (en) | 2017-03-30 | 2017-03-30 | The scramjet engine of fluidized powder propellant |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108708788A (en) * | 2018-05-29 | 2018-10-26 | 中国人民解放军国防科技大学 | Double-combustion-chamber ramjet engine and hypersonic aircraft |
| CN109139293A (en) * | 2018-08-22 | 2019-01-04 | 南京理工大学 | A kind of powder engine powder dispersion device |
| CN109322763A (en) * | 2018-09-19 | 2019-02-12 | 中国人民解放军国防科技大学 | Solid rocket powder scramjet engine |
| CN109630315A (en) * | 2019-02-25 | 2019-04-16 | 中国人民解放军国防科技大学 | Solid rocket scramjet engine, arc-shaped gas generator and central injection device |
| CN109826710A (en) * | 2019-01-31 | 2019-05-31 | 西北工业大学 | Hyperbaric environment powder particle micro-disturbance starts fluidizer |
| CN110318878A (en) * | 2019-06-13 | 2019-10-11 | 内蒙动力机械研究所 | Sky and space plane Active Cooling System based on Magnetohydrodynamic Power bypass |
| CN110510094A (en) * | 2019-07-02 | 2019-11-29 | 杭州电子科技大学 | Fast driving device and its driving method based on powdered reaction |
| CN111594342A (en) * | 2020-04-28 | 2020-08-28 | 西北工业大学 | Air inlet bleed air powder supply device with controllable flow and method |
| CN114112407A (en) * | 2021-12-02 | 2022-03-01 | 内蒙动力机械研究所 | Powder detonation engine conveying system and method |
| RU2767583C1 (en) * | 2021-04-02 | 2022-03-17 | ФЕДЕРАЛЬНОЕ ГОСУДАРСТВЕННОЕ КАЗЕННОЕ ВОЕННОЕ ОБРАЗОВАТЕЛЬНОЕ УЧРЕЖДЕНИЕ ВЫСШЕГО ОБРАЗОВАНИЯ "Военная академия Ракетных войск стратегического назначения имени Петра Великого" МИНИСТЕРСТВА ОБОРОНЫ РОССИЙСКОЙ ФЕДЕРАЦИИ | Method for feeding a nanodispersed component of a fuel composition into the combustion chamber of a ramjet engine |
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Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108708788B (en) * | 2018-05-29 | 2021-07-02 | 中国人民解放军国防科技大学 | Double-combustion-chamber ramjet engine and hypersonic aircraft |
| CN108708788A (en) * | 2018-05-29 | 2018-10-26 | 中国人民解放军国防科技大学 | Double-combustion-chamber ramjet engine and hypersonic aircraft |
| CN109139293A (en) * | 2018-08-22 | 2019-01-04 | 南京理工大学 | A kind of powder engine powder dispersion device |
| CN109322763A (en) * | 2018-09-19 | 2019-02-12 | 中国人民解放军国防科技大学 | Solid rocket powder scramjet engine |
| CN109826710A (en) * | 2019-01-31 | 2019-05-31 | 西北工业大学 | Hyperbaric environment powder particle micro-disturbance starts fluidizer |
| CN109630315A (en) * | 2019-02-25 | 2019-04-16 | 中国人民解放军国防科技大学 | Solid rocket scramjet engine, arc-shaped gas generator and central injection device |
| CN109630315B (en) * | 2019-02-25 | 2020-06-16 | 中国人民解放军国防科技大学 | Solid rocket scramjet engine, arc-shaped gas generator and central injection device |
| CN110318878A (en) * | 2019-06-13 | 2019-10-11 | 内蒙动力机械研究所 | Sky and space plane Active Cooling System based on Magnetohydrodynamic Power bypass |
| CN110318878B (en) * | 2019-06-13 | 2022-08-09 | 内蒙动力机械研究所 | Aerospace plane active cooling system based on magnetofluid energy bypass |
| CN110510094A (en) * | 2019-07-02 | 2019-11-29 | 杭州电子科技大学 | Fast driving device and its driving method based on powdered reaction |
| CN110510094B (en) * | 2019-07-02 | 2020-06-16 | 杭州电子科技大学 | Rapid driving device based on powder reaction and driving method thereof |
| CN111594342A (en) * | 2020-04-28 | 2020-08-28 | 西北工业大学 | Air inlet bleed air powder supply device with controllable flow and method |
| RU2767583C1 (en) * | 2021-04-02 | 2022-03-17 | ФЕДЕРАЛЬНОЕ ГОСУДАРСТВЕННОЕ КАЗЕННОЕ ВОЕННОЕ ОБРАЗОВАТЕЛЬНОЕ УЧРЕЖДЕНИЕ ВЫСШЕГО ОБРАЗОВАНИЯ "Военная академия Ракетных войск стратегического назначения имени Петра Великого" МИНИСТЕРСТВА ОБОРОНЫ РОССИЙСКОЙ ФЕДЕРАЦИИ | Method for feeding a nanodispersed component of a fuel composition into the combustion chamber of a ramjet engine |
| CN114112407A (en) * | 2021-12-02 | 2022-03-01 | 内蒙动力机械研究所 | Powder detonation engine conveying system and method |
| CN114112407B (en) * | 2021-12-02 | 2023-11-03 | 内蒙动力机械研究所 | Powder detonation engine conveying system and method |
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Application publication date: 20170620 |
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