CN101881238A - Air-breathing pulse detonation engine and detonation method thereof - Google Patents
Air-breathing pulse detonation engine and detonation method thereof Download PDFInfo
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- CN101881238A CN101881238A CN2010101978263A CN201010197826A CN101881238A CN 101881238 A CN101881238 A CN 101881238A CN 2010101978263 A CN2010101978263 A CN 2010101978263A CN 201010197826 A CN201010197826 A CN 201010197826A CN 101881238 A CN101881238 A CN 101881238A
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Abstract
The invention discloses an air-breathing pulse detonation engine and a detonation method thereof. An air inlet channel, a mixed evaporator, a detonation chamber and a tailpipe are connected along an air inlet direction in turn, and a leaf valve, a main fuel nozzle and an air discharge cavity are arranged in an air inlet ring cavity along the air inlet direction in turn, wherein the fuel radially injects through the main fuel nozzle; the air discharge cavity and an air discharge tube are communicated through a through hole of a central body bracket to the exterior of an outer wall of the air inlet channel; the leaf valve maintains a forward normally opened state; a detonation tube is arranged in the detonation chamber through a mounting bracket; a drainage tube, an igniter and a heat exchanger are arranged on the detonation tube; a plurality of jet holes are formed on a tail side wall or a tail end face; the igniter is positioned on the front section of the detonation tube; and the drainage tube is gapped in the detonation chamber and near the igniter inside the detonation tube respectively. The air-breathing pulse detonation engine has the advantages of capabilities of reliably working under severe condition, realizing lower forward flow resistance, simultaneously suppressing and using reverse flow and improving the engine thrust, along with simple structure and wide flight range.
Description
Technical field
The present invention relates to technical field of engines, especially a kind of air-breathing pulse detonation engine and method of initiation thereof.
Background technique
Pulse-knocking engine is a kind of new concept engine that utilizes intermittent type or pulsed detonation wave to produce thrust.Different with the detonation burning in the conventional engine (as turbojet engine and piston engine etc.), the combustion process in the pulse-knocking engine is knocking combustion.Detonation circulation relatively, the pinking circulation has the higher thermal efficiency.Pulse-knocking engine unit of fuel consumption rate is low, and operating range is wide, and is simple in structure, and the thrust weight ratio height can adapt to the high-speed flight condition, and maximum flight Mach number can reach 5, is the Aero-Space power system of the tool prospect of generally acknowledging both at home and abroad.
What pinking was different with detonation is, itself has very high boosting capability, pressure ratio can reach 20-40 doubly in air is the mixture of oxygenant before and after the detonation wave, and the strong shock of generation can oppositely be passed intake duct back, thereby detonation combustor is very high to the requirement of intake duct.In order to prevent that the flow oscillations that pinking causes from causing intake duct not start, pulse-knocking engine needs an intake duct/detonation chamber distance piece usually, with stop circuit in the specific period pinking import intake duct into from detonation chamber.According to the implementation of this distance piece, pulse-knocking engine can be divided into two kinds of valve and valveless pulse-knocking engines are arranged.Have in the valve pulse-knocking engine, distance piece is a mechanical valve, is installed between detonation chamber and the intake duct.Detonate in pinking, in propagation and the exhaust process, valve closing, valve open in the filling process.Can bring very big wind-exposuring area in the valve closing process, and the stagnation of air incoming flow also can produce great performance loss.Isolation between valveless pulse-knocking engine intake duct and the detonation chamber realizes by aeroelasticity.This design is not only simple in structure, and has solved the adverse effect that incoming flow stagnation is brought.
It is little that the formation principle of detonation wave requires pneumatic valve to have the forward flow resistance, oppositely the big characteristics of flow resistance.The smooth air inlet of the little assurance pulse-knocking engine of forward intake resistance; The reverse flow resistance is big, forms the effect be similar to sealing, helps the stack of shock wave, forms detonation wave, stops the products of combustion reverse flow to go out motor simultaneously, reduces and suppresses the negative thrust that anti-stream causes.At present all there is the problem that forward flow resistance and anti-current control can not fine solution in the pneumatic valve of pulse-knocking engine.
In addition, also there are a lot of problems in detonating of pulse-knocking engine.The detonation mode of many cycle pulses detonation wave mainly is divided into following two kinds at present: first kind is that single-stage is detonated, form detonation by weak spark and be transformed into pinking again, by optimal design and the use of reinforcement detonation to the pinking transformation structure to seed region, the pinking that can realize upper frequency is detonated, but this method all can be brought huge momentum loss usually, need long detonation to pinking transition distance and time, the engine exhaust time is longer, is unfavorable for the further raising of detonation frequency; Second kind is that jet detonates, generally be to allow the hypersensitivity mixed gas in first small combustion chamber, be lighted, expand, enter main combustion chamber by connecting passage then with main combustion chamber, thereby main combustion chamber is lighted, fitness for purpose is supply system independently, need carry high responsive mixed gas, has increased the complexity and the weight of motor.
In sum, the pulse-knocking engine machine is simple in structure, the thrust weight ratio height, but have valve and valveless pulse-knocking engine all to have very important shortcoming: there is valve pulse-knocking engine valve closing can bring very big wind-exposuring area, produces great performance loss; And there is the problem that forward flow resistance and anti-current control can not fine solution in the pneumatic valve of valveless pulse-knocking engine.
Summary of the invention
In order to overcome the contradiction of prior art pulse-knocking engine forward flow resistance and anti-current control, the invention provides a kind of air-breathing pulse detonation engine, can realize less forward flow resistance, suppress simultaneously and utilize reverse flow, improve motor power.
The technical solution adopted for the present invention to solve the technical problems is: comprise the intake duct 10, detonation chamber 20 and the jet pipe 40 that connect successively along airintake direction, the shell of intake duct and intake duct centerbody 12 have formed a toroidal cavity, it is the air inlet ring cavity, in the air inlet ring cavity, leaf valve 13, several main fuel nozzles 14 and air discharge cavity 15 are installed successively along airintake direction, main fuel nozzle 14 is circumferentially uniform along the intake duct centerbody, fuel oil forms oil curtain by the radially spray of main fuel nozzle in the air inlet ring cavity.Have through hole in the central body bracket, air discharge cavity is communicated with exhaust tube 17 by the through hole of central body bracket 16, and exhaust tube 17 is communicated to outside the intake duct outer wall, and opening direction is consistent with jet pipe 40 directions.Leaf valve 13 keeps the forward normally opens, and promptly incoming flow always can the forward inflow engine, mixture ignition in the detonation chamber, detonate after, the anti-pass shock wave is closed leaf valve, anti-stream can't flow out intake duct, and when the motor internal pressure was reduced under the incoming flow punching press by the time, leaf valve reopened.Between intake duct 10 and detonation chamber 20 blending vaporizer 21 is installed, igniter 22 is positioned at detonation chamber 20 leading portions, perhaps is positioned at detonate tube 30 leading portions, and detonate tube 30 is installed in the detonation chamber 20 by mounting bracket 31.In the time of after the igniter 22 of motor is positioned at detonation chamber 20 leading portion blending vaporizers 21, promptly adopt weak spark igniting single-stage to detonate, do not comprise detonate tube 30, detonate tube support 31, drainage tube 32 and jet hole 34 in the invention this moment.At this moment, heat exchanger 33 also will be installed in detonation chamber afterbody outer wall.But this firing mode can't realize detonating fast of pinking usually, low responsive gas-liquid two-phase (such as the Kerosene) detonation wave that the practical application that particularly is difficult to detonate is fast expected most.In order to accelerate the forming process of detonation wave, the present invention is installed in detonate tube 30 leading portions with igniter 22, after the drainage tube 32, drainage tube one end opening is in detonation chamber 20, come circulation road over against what intake duct and blending vaporizer formed, the other end opening is in detonate tube 30 near the igniter 22 in one times of diameter range of detonate tube.Detonate tube also is in-engine obstacle and heat absorber simultaneously, can promote the fast transition of detonation wave in the detonation chamber 20, also can absorb circulation heat, heated fuel oil and air that many circulations pinking generates.Detonate tube 30 is installed in the detonation chamber 20 by support 31.Drainage tube 32, igniter 22 and heat exchanger 33 are installed on the detonate tube 30, and afterbody sidewall or breech face have some jet holes 34, give the detonate tube independently supplying high responsive fuel oil/oxygenant through starting fuel oil/oxidant inlet 35.Heat exchanger is the thin walled cavity that is installed in detonate tube afterbody outer wall, and its inner chamber is a helical groove structure, and main fuel flows along spiral channel, and is recycled the heat release preheating.
The shell of described intake duct centerbody and intake duct can move forward and backward relatively, thereby changes actual valid circulation area.
Described intake duct centerbody 12 can be designed to be similar to the multistage composite structure of pull antenna, and each intersegmental axial distance is adjustable.Leaf valve 13 is installed in intake duct centerbody 12 stage casings.
Described air discharge cavity 15 is an inner groovy of centerbody tail end, air discharge cavity can be designed to sphere, square or other arbitrary shapes, absorb forward pass shock wave and anti-stream, air discharge cavity is communicated with exhaust tube 17 by central body bracket 16, exhaust tube 17 opening directions are consistent with jet pipe 50, counter flow to air discharge cavity 15 after, flow into exhaust tubes 17 through support 16, discharge motor, thereby utilize anti-miscarriage to give birth to positive thrust.
Described blending vaporizer 21 structures are Venturi tube, and preceding half section is the convergence pipe, and the second half section is an expanding duct, simultaneously, the profile of blending vaporizer and air discharge cavity 15 couplings, the profile extension cord that promptly guarantees the blending vaporizer is in air discharge cavity, guiding refluxes into air discharge cavity, suppresses counter flowing to into intake duct.Air and fuel oil after the blending, further atomize, mix and evaporate under the effect of blending vaporizer 21 in the air inlet ring cavity of air intake casing and centerbody formation.In addition, the blending vaporizer can absorb the cycling hot that many circulations pinking forms, and heats next circuit fresh air and fuel oil.
Described intake duct centerbody adopts supersonic inlet centerbody or subsonics centerbody, air intake casing adopts supersonic inlet shell or subsonics air intake casing, forms supersonic speed pulse-knocking engine intake duct and pneumatic valve system or subsonic speed pulse-knocking engine intake duct and pneumatic valve system respectively.
Be equipped with in the described air discharge cavity 15 along the valve 19 of airintake direction front and back start, valve and air discharge cavity Spielpassung, the structure that adds the detonation chamber internal pressure by electric actuator, hydraulic pressure or spring is controlled, start before and after realizing.Valve 19 is in the air discharge cavity breech face and is its original shut state, and the fuel oil and the air of filling in the motor can not flow to outside the detonation chamber by air discharge cavity; Behind the engine ignition, valve is start forward, and the anti-air discharge cavity of flowing through flows out motor by exhaust tube.
When described detonation chamber internal diameter during greater than 15cm, use the detonate tube of a plurality of parallel arranged, the acceleration knock ripple detonates.
Described main fuel nozzle also can be along circumferentially being distributed on the air intake casing, heat exchanger is installed in main detonation chamber rear end, the main fuel oil circuit (comprise main fuel nozzle oil circuit inlet 18, main fuel inlet 36 and heat exchanger main fuel outlet 37 and between connecting pipeline) be distributed in outside the motor, simplify the engine interior structure.
The method of initiation of described detonate tube comprises two kinds of mode of operations: one, engine start or operating conditions are when abominable (comprising high-altitude flight or maneuvering flight), (" high responsive " is meant the fuel/oxidant mixture that is easy to detonate, such as fuel oil/oxygen mixture, vaporized fuel/air mixture etc. to give the high responsive fuel oil/oxidant mixture of detonate tube independently supplying through starting fuel oil/oxidant inlet 35.), the igniter igniting, the detonate tube reliable initiation, the pinking jet sprays into detonation chamber 20 by the jet hole 34 of sidewall or tail end, and main detonation chamber fast detonates.(operating time is 10～40s, and the concrete time is relevant with the detonate tube detonation frequency, and frequency is high more after work a period of time like this, time is short more), engine wall surface temperature rising, particularly detonate tube temperature very high (reaching 500 ℃), and the detonate tube back segment is equipped with heat exchanger 33.Fuel oil after the heating can evaporate faster, and meanwhile, the also launched machine wall of incoming flow air heat is heated, and these have all improved the explosiveness of main fuel/air.At this moment, the high responsive fuel oil/oxygenant of stop supplies, detonate tube enters second kind of mode of operation.Main fuel after the preheating (such as aviation kerosine or aviation gasoline) flows into main fuel nozzle 14 by the road, intake port injection and with the incoming flow blending, strengthen blending and evaporation through blending vaporizer 21 afterwards, part mixture flows into detonate tube through drainage tube 32, light a fire through igniter, realize quick-friedly in advance, the pinking jet sprays into detonation chamber 20 by the jet hole 34 of sidewall or tail end, and main detonation chamber detonates.After main detonation chamber detonates, heat exchanger 33 will be heated simultaneously by detonate tube and main detonation chamber, and the pre-heat effect of main fuel is better.
The invention has the beneficial effects as follows: intake duct 10, blending vaporizer 21 and detonate tube 30 that the present invention adopts are characterized in all effectively suppressing and utilizing anti-stream.Its principle is that the profile of blending vaporizer 21 can be returned detonation chamber from the shock wave reflection that detonation chamber 20 oppositely transmits with a part, simultaneously another part shock wave is introduced air discharge cavity 15, diffraction takes place and decay, the high-pressure gas that enters in the air discharge cavity 15 flows into exhaust tube 17 through support 16, enter atmosphere in the same way with jet pipe 40, thereby utilize anti-miscarriage to give birth to forward thrust.Through the decay of blending vaporizer 21 and air discharge cavity 15, shock strength enters the air inlet ring cavity after descending, and drives reed, closes leaf valve, makes anti-stream can't flow out intake duct.Meanwhile, use detonate tube can quicken main detonation chamber and form pinking, pinking fringe time and distance have been shortened, therefore detonation chamber length can be shortened greatly, the extensional wave that forms of detonation chamber exhaust time of passing to intake duct greatly reduces like this, can pull up to the forward pass shock wave, make anti-stream flow to jet pipe 40 again.
In many cyclic processes, intake duct 10, detonation chamber 20, blending vaporizer 21 and detonate tube 30 are heated in combustion process, liquid fuel through after heat exchanger 33 preheatings by 14 sprays of main fuel nozzle, with the air that is heated by intake duct after the air inlet ring cavity mixes, by intake duct and the further preheating of blending vaporizer, enter detonation chamber 20 and detonate tube, it is higher that drop partly or completely evaporates the vapour tension of fuel in the mixture of formation, is convenient to igniting and detonates.Needed ignition delay time was less after igniter 22 discharged in the ignition mixture of this premix, detonate tube 30 internal diameters are much smaller than main combustion chamber, the speed that igniting back pressure rises is apparently higher than the rate of pressure rise of main detonation chamber direct ignition, thereby velocity of propagation of flame can and reach the combustion gas choking velocity in short distance in the time, thereby form shock wave fast, and then initial detonation wave.The shock wave of multiply High Temperature High Pressure jet and generation thereof is become owner of detonation chamber from the detonate tube injection, in main detonation chamber, form High Temperature High Pressure focus and confined explosion, simultaneously because the turbulent flow of main combustion chamber inner height development, make the very fast formation of pinking, and propagate to two ends at a terrific speed.Detonate tube 30 provides the igniting of high-energy jet except piloting engine, outside the pre-heating oil, it itself also is the sensitization obstacle of main detonation chamber, can help detonation chamber to form high-intensity turbulent flow and complicated shock wave reflection, collision etc., quicken main detonation chamber and form detonation wave.
The present invention has obtained can be at the high-speed pulse pinking advancing means of reliably working under the mal-condition, simple in structure, the flight range broadness, can realize less forward flow resistance, suppress simultaneously and utilize reverse flow, improve motor power, can be used as the power plant of high speed model plane, unmanned plane, target drone, subsonic velocity cruise missile and small boat etc.
The present invention is further described below in conjunction with drawings and Examples.
Description of drawings
Fig. 1 is a section of structure of the present invention, and Fig. 1 (b) is the sectional view of half-twist shown in Fig. 1 (a).
Fig. 2 (a) and (b) be respectively band air discharge cavity valve and be not with valve pinking mixture filling mixed process schematic representation.
Fig. 3 is that the air inlet pneumatic valve system suppresses and the anti-stream of utilization principle sequential chart.
Intake duct and detonation chamber leading portion shock wave and mobility status schematic representation when Fig. 3 (a) forms for pinking.
Fig. 3 (b) is for after pinking forms, and the intake duct schematic representation is oppositely imported in shock wave and mobile beginning into.
Fig. 3 (c) is the shock wave and the further backpropagation of flowing, and enters the air discharge cavity schematic representation.
Fig. 3 (d) arrives detonation chamber leading portion schematic representation for the extensional wave anti-pass.
Fig. 3 (e) is the further anti-pass of extensional wave, enters air inlet ring cavity schematic representation.
Fig. 3 (f) be the extensional wave anti-pass to leaf valve, anti-stream flows to the jet pipe schematic representation again.
Fig. 4 is the detonate tube detonation chamber principle sequential schematic representation that detonates.
Fig. 4 (a) is a plug ignition in the detonate tube, generates detonation wave, imports the detonation chamber schematic representation into.
The pinking jet that Fig. 4 (b) detonate tube the spreads out of ignition mixture schematic representation in the detonation chamber that detonates.
Among the figure, 10. intake duct, 11. air intake casings, 12. intake duct centerbodies, 13. leaf valve, 14. main fuel nozzles, 15. air discharge cavity, 16. central body bracket, 17. exhaust tube, 18. main fuel nozzle oil circuits inlet, 19. air discharge cavity valves, 20. detonation chambers, 21. the blending vaporizer, 22. igniters, 30. detonate tubes, 31. detonate tube supports, 32. drainage tube, 33. heat exchangers, 34. jet holes, 35. starting fuel oil/oxidant inlets, 36. the main fuel inlet, the outlet of 37. heat exchanger main fuels, 40. jet pipes.
Embodiment
Motor has the separate air inlet oil-feed system of two covers, intake duct, detonation chamber, detonate tube and a jet pipe, and intake duct 10 is positioned at the front end of motor, opening forward, as Fig. 1 (a), comprise air intake casing 11, intake duct centerbody 12, leaf valve 13, main fuel nozzle 14, air discharge cavity 15, exhaust tube 17 and main fuel nozzle oil circuit inlet 18, central body bracket 16 is distributed in different circumferential positions with main fuel nozzle 14, so does not have central body bracket among Fig. 1.On the sectional drawing 1 (b) of another direction (half-twist), air intake casing 11 links to each other with intake duct centerbody 12 by the central body bracket 16 of a plurality of circumference uniform distributions.Air intake casing 11 maintains static, can be by regulating the size that intake duct centerbody 12 front and back axial positions are regulated the air inlet ring cavity, and then regulate air mass flow.Intake duct centerbody 12 can be designed to the multistage composite structure, and each intersegmental axial distance is adjustable, to satisfy complicated operating conditions.A plurality of main fuel nozzles 14 are distributed on the intake duct centerbody 12, and number of nozzle is determined according to the size and the maximum operation frequency of motor.Fuel oil flows into main fuel nozzle oil circuit inlet 18 oil circuits through intake duct centerbody 12 inside by heat exchanger 33 outlets 37, is radially sprayed with certain angle and granularity by main fuel nozzle 14 again.Air discharge cavity 15 is positioned at intake duct centerbody 12 tail ends, is communicated with exhaust tube 17 by the duct in the central body bracket 16.Exhaust tube 17 quantity can be measured a plurality of symmetrical distributions according to size of engine and venting.
Use among the embodiment of air discharge cavity valve 19, as Fig. 2 (a), when further the mixture after the blending evaporation flows into detonation chamber 20, main flow is toward the detonation chamber downstream flow, partially mixed thing flows into detonate tube 30 through drainage tube 32, drainage tube quantity is determined by the own size of detonate tube size, frequency of okperation and drainage tube, generally is uniform more than 2, has only drawn one among this figure to illustrate.Drainage tube 32 both ends opens, an end are positioned at blending vaporizer runner over against coming flow path direction, and an end stretches near detonate tube 30 igniters 22 one times of diameter of detonate tube.Similar with the blending vaporizer, drainage tube and detonate tube, particularly detonate tube can absorb the portion of energy of a cyclic high-temperature combustion gas and heat, and the further mixture in the preheating detonate tube helps follow-up igniting and detonates.Meanwhile, blending vaporizer, detonate tube and heat exchanger etc. also are the enhanced detonation transformation structure in the main detonation chamber, and fuel/air can form a large amount of vortex streets and flow and body-shedding vortex when filling, strengthened the mixed process of fuel/air.Also can change the runner size of 21 in intake duct centerbody 12 and blending vaporizer by the axial position of regulating air discharge cavity valve 19, regulate the fuel/air mixture flow rate that enters detonation chamber, and then adjust the engine operation frequency, regulate motor power.
Among the embodiment of air discharge cavity valveless, as Fig. 2 (b), when further the mixture after the blending evaporation flows into detonation chamber 20, main flow is toward the detonation chamber downstream flow, partially mixed thing flows into detonate tube 30 through drainage tube 32, also has spiece to flow into exhaust tube 17 through air discharge cavity 15, discharges motor.
When engine start and operating mode are abominable, infeed high responsive fuel oil/oxygenant by the high responsive fuel oil/oxidant flow channel of starting fuel oil/oxidant inlet 35 in detonate tube support 31 to detonate tube, open igniter 22 simultaneously, detonate tube fast detonates.Igniter 22 and corresponding ignition system can be selected conventional low-yield automobile spark ignition system for use, also can select other high-frequency ignition systems such as plasma ignition.Igniter 22 and line system thereof are arranged in the detonate tube fore poppet, and fore poppet is positioned at after the drainage tube 32, and igniter 22 discharge ends vertically screw in the detonate tube leading portion, arrange as Fig. 1 (b).After detonate tube work a period of time, heat exchanger 33 utilizes the main fuel in the circulation used heat preheating heat exchanger, and meanwhile, the also launched machine wall of incoming flow air heat is heated, and has improved the explosiveness of main fuel/air.So, close starting fuel oil/oxidant inlet 35, can quick-fried mixture by the drainage tube supply, detonate tube changes normal mode of operation over to.Usual heat-exchanger 33 is welded on outside detonate tube 30 posterior segments, because knocking combustion in the detonate tube and the knocking combustion in the main detonation chamber all can cause the detonate tube wall surface temperature to raise,, need cooling so the detonate tube wall surface temperature is the highest, improve the life-span, can provide the highest exchange capability of heat simultaneously.Heat exchanger can have various ways, and this example provides a kind of housing that has inner spiral groove, and the rear and front end links to each other with main fuel nozzle oil circuit inlet 18 with main fuel inlet 36 respectively.Fuel oil enters heat exchanger from main fuel inlet 36 main fuel stream in detonate tube support 31, and the fuel oil of preheating leads to main fuel nozzle oil circuit inlet 18 by heat exchanger fuel outlet 37.
Initiation process is shown in Fig. 4 (a) and 4 (b), the pinking jet is injected detonation chamber through the jet hole 34 of detonate tube sidewall or tail end, and lighting in the main detonation chamber can quick-fried mixture, and forms High Temperature High Pressure focus and confined explosion, make the very fast formation of pinking, and propagate to two ends at a terrific speed.When main detonation chamber internal diameter is big, can use many detonate tubes, utilize more pinking jet to quicken main detonation chamber and detonate.
Motor generation effective push is discharged in the detonation wave and the combustion gas that flow to jet pipe 40, the shock wave of backpropagation and combustion gas are under the effect of blending vaporizer 21, part shock wave and combustion gas are reflected back, part shock wave and combustion gas enter and jet pipe opening exhaust tube 17 in the same way through air discharge cavity 15, discharge motor, produce effective positive thrust, remaining shock wave that is attenuated and combustion gas enter the air inlet ring cavity, the actuating spring valve leaf is closed runner, can't discharge intake duct.Meanwhile, because the use of detonate tube is detonated in the main detonation chamber fast, detonation chamber length is shorter, and the extensional wave that the detonation chamber exhaust forms is constantly propagated forward, and pulls up to the forward pass shock wave in intake duct, makes that the air-flow in the intake duct flows to detonation chamber again.Its principle is shown in Fig. 3 (a)-3 (f).Thereby suppress and utilized anti-stream, improve motor power.
The motor oil mass is calculated according to flying speed and frequency of okperation, and its control can be adopted electric jet technology or adopt pressure control.Open starting fuel oil/oxidant inlet 35 during engine start earlier, infeed high sensitivity/oxygenant to detonate tube 30, open ignition system simultaneously, detonate fast, and the injection air enters main detonation chamber 20, injection volume is relevant with detonate tube frequency of okperation and size.After detonate tube work a period of time, the main fuel oil circuit is opened, and closes starting fuel oil/oxidant inlet 35 then, adjusts the detonate tube spark rate according to the incoming flow flow, and motor detonates.Motor enters the pulse-knocking operation mode, and along with the progressively increase of speed, charge flow rate increases, and increases fuel flow thereupon and improves spark rate, and thrust increases, and flying speed continues to increase, until reaching design point.The thrust size can also be controlled by the size of air inlet ring cavity, corresponding simultaneously fuel flow and the spark rate regulated.When increasing the circulation area of air inlet ring cavity, the incoming flow flow increases, and the corresponding fuel flow that increases improves spark rate, so thrust increases, vice versa.
Claims (9)
1. air-breathing pulse detonation engine, comprise the intake duct, detonation chamber and the jet pipe that connect successively along airintake direction, it is characterized in that: the shell of intake duct and intake duct centerbody have formed a toroidal cavity, it is the air inlet ring cavity, in the air inlet ring cavity, leaf valve, several main fuel nozzle and air discharge cavity are installed successively along airintake direction, the main fuel nozzle is circumferentially uniform along the intake duct centerbody, and fuel oil forms oil curtain by the radially spray of main fuel nozzle in the air inlet ring cavity; Have through hole in the central body bracket, air discharge cavity is communicated with exhaust tube by the through hole of central body bracket, and exhaust tube is communicated to outside the intake duct outer wall, and opening direction is consistent with the jet pipe direction; Leaf valve keeps the forward normally open; The blending vaporizer is installed between intake duct and detonation chamber, detonate tube is installed in the detonation chamber by mounting bracket, drainage tube, igniter and heat exchanger are installed on the detonate tube, afterbody sidewall or breech face have some jet holes, give the detonate tube independently supplying high responsive fuel oil/oxygenant through starting fuel oil/oxidant inlet; Igniter is positioned at the detonate tube leading portion, and drainage tube one end opening comes circulation road over against what intake duct and blending vaporizer formed in detonation chamber, and the other end opening is in detonate tube near the igniter in one times of diameter range of detonate tube; Heat exchanger is the thin walled cavity that is installed in detonate tube afterbody outer wall, and its inner chamber is a helical groove structure, and main fuel flows along spiral channel, and is recycled the heat release preheating.
2. a kind of air-breathing pulse detonation engine according to claim 1 is characterized in that: the shell of described intake duct centerbody and intake duct can move forward and backward relatively.
3. a kind of air-breathing pulse detonation engine according to claim 1 is characterized in that: described intake duct centerbody is the multistage composite structure, and each intersegmental axial distance is adjustable; Leaf valve is installed in intake duct centerbody stage casing.
4. a kind of air-breathing pulse detonation engine according to claim 1 is characterized in that: described blending evaporation structure is a Venturi tube, and preceding half section is the convergence pipe, and the second half section is an expanding duct, the profile of blending vaporizer and air discharge cavity coupling.
5. a kind of air-breathing pulse detonation engine according to claim 1, it is characterized in that: described intake duct centerbody adopts supersonic inlet centerbody or subsonics centerbody, air intake casing adopts supersonic inlet shell or subsonics air intake casing, forms supersonic speed pulse-knocking engine intake duct and pneumatic valve system or subsonic speed pulse-knocking engine intake duct and pneumatic valve system respectively.
6. a kind of air-breathing pulse detonation engine according to claim 1, it is characterized in that: be equipped with in the described air discharge cavity along the valve of airintake direction front and back start, valve and air discharge cavity Spielpassung, the structure that adds the detonation chamber internal pressure by electric actuator, hydraulic pressure or spring is controlled, start before and after realizing.
7. a kind of air-breathing pulse detonation engine according to claim 1 is characterized in that: described detonation chamber internal diameter uses the detonate tube of a plurality of parallel arranged during greater than 15cm.
8. a kind of air-breathing pulse detonation engine according to claim 1 is characterized in that: described main fuel nozzle is along circumferentially being distributed on the air intake casing, and heat exchanger is installed in main detonation chamber rear end, and the main fuel oil circuit is distributed in outside the motor.
9. the method for initiation of the described air-breathing pulse detonation engine of claim 1, when it is characterized in that comprising the steps: engine start, high-altitude flight or maneuvering flight, give the detonate tube independently supplying high responsive fuel oil/oxidant mixture through starting fuel oil/oxidant inlet, comprise fuel oil/oxygen mixture or vaporized fuel/air mixture, the igniter igniting, the detonate tube reliable initiation, the pinking jet sprays into detonation chamber by the jet hole of sidewall or tail end, and main detonation chamber fast detonates; Like this behind work 10～40s, the high responsive fuel oil/oxygenant of stop supplies, main fuel after the preheating flows into the main fuel nozzle by the road, intake port injection and with the incoming flow blending, strengthen blending and evaporation through the blending vaporizer afterwards, a part of mixture flows into detonate tube through drainage tube, light a fire through igniter, realize quick-friedly in advance, the pinking jet sprays into detonation chamber by the jet hole of sidewall or tail end, and main detonation chamber detonates.
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| JP2015036528A (en) * | 2013-08-12 | 2015-02-23 | 株式会社Ｉｈｉエアロスペース | Port cover opening device |
| CN104612821A (en) * | 2015-01-28 | 2015-05-13 | 南京理工大学 | One-way priming device of probing type rotation detonation engine |
| WO2016062155A1 (en) * | 2014-10-19 | 2016-04-28 | 赵晴堂 | Array multi-point set explosion-type pulse detonation engine |
| CN106988927A (en) * | 2017-05-22 | 2017-07-28 | 西南交通大学 | A kind of high-frequency pulse injection device |
| CN107218155A (en) * | 2017-06-06 | 2017-09-29 | 陈蜀乔 | A kind of pulse in advance ignite can steady operation detonation engine |
| CN108825384A (en) * | 2018-08-27 | 2018-11-16 | 西北工业大学 | A kind of air-fuel mixture starter |
| CN109441636A (en) * | 2018-12-21 | 2019-03-08 | 中国人民解放军空军工程大学 | A kind of axial direction repairing cracker |
| CN109667685A (en) * | 2018-12-26 | 2019-04-23 | 中国人民解放军战略支援部队航天工程大学 | The continuous pinking airbreathing motor and aircraft of variable thrust |
| CN109723554A (en) * | 2018-12-21 | 2019-05-07 | 中国人民解放军空军工程大学 | A kind of central distribution plasma pyrolysis activation recharging oil device and method |
| CN109882315A (en) * | 2019-03-21 | 2019-06-14 | 中国航发湖南动力机械研究所 | Pulse-knocking engine |
| CN110259601A (en) * | 2019-06-23 | 2019-09-20 | 西北工业大学 | A kind of detonation chamber of pulse detonation engine structure and the method for ignition |
| CN110778419A (en) * | 2019-10-14 | 2020-02-11 | 哈尔滨工程大学 | Detonating device for detonation combustor |
| CN111520767A (en) * | 2020-06-03 | 2020-08-11 | 西安热工研究院有限公司 | Pulse detonation combustion chamber capable of adjusting energy distribution of outlet gas |
| CN111828175A (en) * | 2020-06-13 | 2020-10-27 | 中国人民解放军空军工程大学 | Pre-combustion heating device and rotary detonation engine using same |
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