CN103899435B - A kind of combined type pulse detonation engine detonation chamber - Google Patents
A kind of combined type pulse detonation engine detonation chamber Download PDFInfo
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- CN103899435B CN103899435B CN201410123565.9A CN201410123565A CN103899435B CN 103899435 B CN103899435 B CN 103899435B CN 201410123565 A CN201410123565 A CN 201410123565A CN 103899435 B CN103899435 B CN 103899435B
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Abstract
The invention discloses a kind of combined type pulse detonation engine detonation chamber, adopt two-stage shock wave focus device and pre-explosion pipe igniting compound mode; Main detonation chamber is connected with motor, and the first pre-explosion pipe and the second pre-explosion pipe are fixed on the both sides of motor, by the first jet pipe and the installation parallel with main detonation chamber respectively of the second jet pipe; The pinking jet that jet pipe is drawn from pre-explosion pipe outlet, gas mixture through fully mixing and atomization first fills main detonation chamber and shock wave focus cavity, after filling, draw pinking jet from pre-explosion pipe and enter detonation chamber by the outlet of jet pipe, the gas mixture ignited in detonation chamber, forms the deflagration wave forward direction of the leading shock wave of band.Deflagration wave forms strong shock under the effect of guide ring, and strong shock ignites and can form detonation wave and produce larger positive thrust by quick-fried oil gas mixture; Realize detonation chamber of pulse detonation engine to detonate in comparatively short distance, thus shorten the length of motor, improve the frequency of okperation of pulse-knocking engine.
Description
Technical field
The invention belongs to detonation engine technical field, specifically, relate to a kind of combined type pulse detonation engine detonation chamber.
Background technique
Detonation wave is utilized to comprise oblique detonation engine to the propulsion system producing thrust, rotate detonation engine, pulse-knocking engine, two-stage pulse-knocking engine etc.Pulse-knocking engine utilizes periodic detonation wave to produce the propulsion system of thrust.General pulse-knocking engine produces deflagration ripple by plug ignition, and deflagration ripple forms the focus of local after obstacle accelerates, and the High Temperature High Pressure district of detonation wave of namely overdriving, then forms stable detonation wave forward direction.But flame acceleration needs to grow very much a segment distance to the focus forming local, thus limits the frequency of okperation of motor.What pre-explosion pipe adopted is oxygenant and the fuel of the self-contained gaseous state easily detonated or liquid state, can detonate in very short distance, and the method that the detonation wave that pre-explosion pipe produces is transitioned into main detonation chamber to detonate is called the method that pre-explosion pipe is lighted a fire.The method utilizing pre-explosion pipe to light a fire can shorten distance of detonating, but wants the changeover portion between appropriate design pre-explosion pipe and main detonation chamber.Another scheme utilizing pre-explosion pipe to light a fire draws one thermojet to light main detonation chamber from pre-explosion pipe, and then flame finally forms detonation wave at main detonation chamber after one section of obstacle accelerates.
The difference of two-stage pulse-knocking engine and general pulse-knocking engine is that it utilizes shock wave to converge to produce detonation wave, high-speed flame is produced by precombustion chamber fuel-rich combustion, then high-speed flame forms annular jet with poly-heart mode incidence by guide ring, after concave surface chamber focuses on, form strong shock, the High Temperature High Pressure produced by strong shock is detonated the fuel gas mixture after fuel-rich combustion.
Although the frequency of okperation of two-stage pulse-knocking engine is very high, can reach tens Kilohertzs in theory, existing experimental research shows, the combustion mode in concave surface chamber, mainly based on detonation, does not form high frequency pinking.Reason is wherein many-sided, and the burning as precombustion chamber could not produce the flammable mixed gas of high temperature Small molecular being rich in activation base, and shock wave focus cavity concave surface is not optimum form.At present, major part mainly concentrates in numerical simulation about the research work of two-stage pulse-knocking engine.
Summary of the invention
In order to avoid the deficiency that prior art exists, the present invention proposes a kind of combined type pulse detonation engine detonation chamber, adopt two-stage shock wave focus device and pre-explosion pipe igniting compound mode, realize detonation chamber of pulse detonation engine to detonate in comparatively short distance, thus shorten the length of motor, improve the frequency of okperation of pulse-knocking engine.
The technical solution adopted for the present invention to solve the technical problems is: comprise motor, first pre-explosion pipe, second pre-explosion pipe, its feature is also to comprise main detonation chamber, flange, first jet pipe, second jet pipe, first jet pipe outlet, second jet pipe outlet, pole, shock wave focus cavity, oblique fire discharge orifice, guide ring, jet pipe, main detonation chamber is connected by flange with motor, first pre-explosion pipe and the second pre-explosion pipe lay respectively at the both sides of motor, and by the first jet pipe and the installation parallel with main detonation chamber respectively of the second jet pipe, two jet pipe one end are positioned at main detonation chamber, two jet pipe end sidewalls have the first jet pipe outlet and the outlet of the second jet pipe, jet pipe exit opening direction is consistent with airintake direction, the other end of two jet pipes lays respectively in the first pre-explosion pipe and the second pre-explosion pipe, the end sidewalls of two jet pipes has pinking jet conduction hole, the pinking jet conduction hole center of circle and pre-explosion pipe central axis, shock wave focus cavity is positioned at main detonation chamber inner outlet position, is connected by pole and main detonation chamber, and guide ring is positioned at main detonation chamber outlet end, is fixedly connected with main detonation chamber by screw thread, and jet pipe is arranged on guide ring by bolt, described shock wave focus cavity is parabolic type, and cavity wall hoop is evenly equipped with multiple oblique fire discharge orifice, and oblique fire discharge orifice central axis gathers the focus in parabolic type cavity.
The two ends distance that first jet pipe and the second jet pipe are positioned at main detonation chamber is greater than 1/2 of main detonation chamber radius, but is less than the radius of main detonation chamber.
First jet pipe outlet is identical with two jet pipe internal diameters with the aperture of the second jet pipe outlet.
The ratio of the cross-section area of shock wave focus cavity and the cross-section area of main detonation chamber is 1/2 ~ 1/3.
The channelization angle of guide ring is greater than 5 degree.
Beneficial effect
The combined type pulse detonation engine detonation chamber that the present invention proposes, adopts two-stage shock wave focus device and pre-explosion pipe igniting compound mode; Main detonation chamber is connected with motor and communicates, and the first pre-explosion pipe and the second pre-explosion pipe lay respectively at the both sides of motor, and by the first jet pipe and the installation parallel with main detonation chamber respectively of the second jet pipe; The pinking jet that jet pipe is drawn from pre-explosion pipe outlet, gas mixture through fully mixing and atomization first fills main detonation chamber and shock wave focus cavity, after filling, draw pinking jet from pre-explosion pipe and enter main detonation chamber from jet pipe outlet, the gas mixture ignited in main detonation chamber, forms the deflagration wave forward direction of the leading shock wave of band.Deflagration wave, under the effect of guide ring, forms two strands to heart jet, converges generation strong shock to heart jet in the concave surface collision of shock wave focus cavity, and strong shock ignites and can form detonation wave and produce larger positive thrust by quick-fried gas mixture.Detonation wave is propagated to jet pipe, after jet pipe expands, produce thrust, realizes detonation chamber of pulse detonation engine and detonates in comparatively short distance, thus shorten the length of motor, improve the frequency of okperation of pulse-knocking engine.
Accompanying drawing explanation
Below in conjunction with drawings and embodiments, a kind of combined type pulse detonation engine of the present invention detonation chamber is described in further detail.
Fig. 1 is combined type pulse detonation engine detonation chamber structural representation of the present invention.
Fig. 2 is shock wave focus cavity of the present invention and guide ring structural representation.
Fig. 3 is embodiments of the invention 1 structural representations.
Fig. 4 is embodiments of the invention 2 structural representations.
In figure:
1. main detonation chamber 2. flange 3. first jet pipe 4. second jet pipe 5. first jet pipe outlet 6. second jet pipes export 7. pole 8. shock wave focus cavitys 9. and slant discharge orifice 10. guide ring 11. jet pipe 12. intake duct 13. orifice plate 14. first pre-explosion pipe fuel inlet 15. first pre-explosion pipe 16. second pre-explosion pipe fuel inlet 17. second pre-explosion pipe 18. pinking intensifier 19. pinking jet conduction hole 20. motor 21. first groups of pre-explosion pipes 22. second groups of pre-explosion pipes
Embodiment
Embodiment 1
The present embodiment is the first preferred version, and two jet pipes can timesharing ignition operation; Namely two pre-explosion pipes are sequentially fired successively, make the frequency of okperation of main detonation chamber be the twice of pre-explosion pipe frequency of okperation, thus improve the frequency of okperation of motor greatly.
Consult Fig. 1, Fig. 2, Fig. 3, the present embodiment combined type pulse detonation engine detonation chamber, by main detonation chamber 1, flange 2, first jet pipe 3, second jet pipe 4, first jet pipe outlet 5, second jet pipe outlet 6, pole 7, shock wave focus cavity 8, oblique fire discharge orifice 9, guide ring 10, jet pipe 11, intake duct 12, orifice plate 13, first pre-explosion pipe fuel inlet 14, first pre-explosion pipe 15, second pre-explosion pipe fuel inlet 16, second pre-explosion pipe 17, pinking intensifier 18, pinking jet conduction hole 19, motor 20 forms, main detonation chamber 1 and motor 20 are connected by flange 2 and communicate, first pre-explosion pipe 15 and the second pre-explosion pipe 17 are separately fixed at the both sides of motor 20, and by the first jet pipe 3 and the second jet pipe 4 respectively with the parallel installation of main detonation chamber 1, one end of two jet pipes is fixed in main detonation chamber 1, two jet pipe end sidewalls have the first jet pipe outlet 5 and the second jet pipe outlet 6, jet pipe exit opening direction is consistent with airintake direction, the other end of the first jet pipe 3 and the second jet pipe 4 is separately fixed in the first pre-explosion pipe 15 and the second pre-explosion pipe 17, the end sidewalls of two jet pipes has pinking jet conduction hole 19, pinking jet conduction hole 19 center of circle and pre-explosion pipe central axis.Shock wave focus cavity 8 is arranged on main detonation chamber 1 inner outlet position, is fixedly connected with main detonation chamber 1 by pole 7; Guide ring 10 is fixed on main detonation chamber 1 outlet end, and is threaded connection with main detonation chamber 1, and jet pipe 11 is arranged on guide ring 10 by bolt.Shock wave focus cavity 8 is parabolic type, and cavity wall hoop is evenly equipped with multiple oblique fire discharge orifice 9, and oblique fire discharge orifice 9 central axis gathers the focus in parabolic type cavity.The oblique fire stream slanting discharge orifice in filling process can accelerate gas mixture in cavity 8 and fill, simultaneously, deflagration wave forms multiply by oblique fire discharge orifice 9 and gathers the jet interactions that heart jet and guide ring guide, produce strong shock, the High Temperature High Pressure that strong shock produces makes chemical reaction rate increase, the thermal discharge of chemical reaction increases, and defines hot localised points and promotes that deflagration wave changes to detonation wave.Deflagration wave is formed multiply gathered heart jet by oblique fire discharge orifice 9, strengthens the turbulivity of zone of combustion, accelerates high-temperature fuel gas and does not fire the blending of product, be of value to the formation of detonation wave.The channelization angle of guide ring 10 and the inclined-plane of guide ring and radial direction angulation are greater than 5 degree, thus play good guide functions, the deflagration wave of the leading shock wave of pilot tape converges to cavity, makes the gas mixture that the shock wave converging rear generation can detonate in cavity.
The end of the first pre-explosion pipe 15 has the first pre-explosion pipe fuel inlet 14, the end of the second pre-explosion pipe 17 has the second pre-explosion pipe fuel inlet 16, two independently solenoid valve control the filling of oxygenant and fuel in the first pre-explosion pipe 15 and the second pre-explosion pipe 17 respectively, thus control the frequency of okperation of two pre-explosion pipes.Being respectively equipped with pinking intensifier 18 for accelerating flame in first pre-explosion pipe 15 and the second pre-explosion pipe 17, ensureing that pre-explosion pipe goes out interruption-forming detonation wave, improve the frequency of okperation of pulse-knocking engine.
During engine operation, the intake duct 12 flowing through motor enters main detonation chamber 1 and fully mixes with fuel oil, in order to ensure the abundant mixing of the fuel-air entering main detonation chamber 1, orifice plate 13 is installed to strengthen atomization and the blending of liquid fuel above at main detonation chamber 1.After main detonation chamber 1 is filled, from the pinking jet that pre-explosion pipe attracts, main detonation chamber 1 is lighted a fire, the deflagration wave of the leading shock wave of two strand is formed at main detonation chamber 1, deflagration wave continues forward direction after walking around the outer surface of shock wave focus cavity 8, jet is formed under the effect of guide ring 10, and poly-heart jet interactions interior with cavity 8, final formation one strong shock the gas mixture in cavity of detonating forms detonation wave, detonation wave is propagated to jet pipe under the effect of wall, discharges at a high speed after jet pipe expands.
Embodiment 2
As shown in Figure 4, as the second preferred version of the present invention, jet pipe number can have multiple, and under the permission of bulk, form crossed-symmetrical layout according to axle centered by motor 20, this crossed-symmetrical layout can ensure the formation of detonation wave.In addition, more jet pipe can be divided into many groups, the sequentially fired work successively of each group jet pipe.Start the frequency of okperation of owner's detonation chamber to be the number that the frequency of okperation of pre-explosion pipe is multiplied by grouping again, thus greatly improve the frequency of okperation of motor.In the present embodiment four pre-explosion pipes are divided into two groups, two groups of pre-explosion pipes adopt the means of fixation of crossed-symmetrical, two relative pre-explosion pipes are one group, and two groups of pre-explosion pipes control the filling of fuel and oxygenant respectively by solenoid valve, thus accurately control the igniting of main detonation chamber 1.When first group of pre-explosion pipe 21 starts to light a fire to main detonation chamber 1, second group of pre-explosion pipe 22 is just in the stage of filling.When second group of pre-explosion pipe 22 starts to light a fire to main detonation chamber 1, first group of pre-explosion pipe 21 is in the filling stage, first group of pre-explosion pipe 21 and second group of pre-explosion pipe 22 are alternately lighted a fire to main detonation chamber 1, the frequency of okperation of main detonation chamber 1 is the twice of pre-explosion pipe frequency of okperation, thus greatly improves the frequency of okperation of motor.
Embodiment 3
As the third preferred version of the present invention, jet pipe circularizes layout around main detonation chamber 1, and this annular layout form makes pre-explosion pipe become a kind of little booster, as the assist device of motor supersonic flight.
Combined type pulse detonation engine detonation chamber of the present invention operationally, pre-explosion pipe becomes separately a system, be packed into fuel pre-explosion pipe from the first pre-explosion pipe fuel inlet 14 and the second pre-explosion pipe fuel inlet 16 and oxygenant is accurately controlled by solenoid valve, realize the accurate control of main detonation chamber 1 firing time.Main detonation chamber 1 is in working unit circulation, the fuel air mixture of abundant mixing and atomization starts to fill main detonation chamber 1, after main detonation chamber 1 is filled, the detonation wave that pre-explosion pipe is formed starts to light a fire to main detonation chamber by the first jet pipe 3 and the second jet pipe 4.Deflagration wave is formed at main detonation chamber, deflagration wave forms strong shock and forms localized hyperthermia zone of high pressure with the poly-heart jet interactions that oblique fire discharge orifice 9 is formed after shock wave focus cavity 8 focuses on, then change detonation wave into discharge to jet pipe 11, and on cavity, produce very large thrust.Detonation wave is discharged at a high speed after jet pipe 11 fully expands, and reflects multiple tracks extensional wave and propagate to main detonation chamber 1, reduces the pressure in main detonation chamber 1.After exhaust process terminates, main detonation chamber restarts to fill fresh fuel oil and air mixture; After filling, the pinking jet that pre-explosion pipe is formed also just enters main detonation chamber 1 by the first jet pipe 3 and the second jet pipe 4, and main detonation chamber 1 starts next work cycle.
Claims (5)
1. a combined type pulse detonation engine detonation chamber, comprise motor, first pre-explosion pipe, second pre-explosion pipe, main detonation chamber, first jet pipe, first jet pipe outlet, jet pipe, characterized by further comprising the second jet pipe, second jet pipe outlet, pole, shock wave focus cavity, oblique fire discharge orifice, guide ring, flange, main detonation chamber is connected by flange with motor, first pre-explosion pipe and the second pre-explosion pipe lay respectively at the both sides of motor, and by the first jet pipe and the installation parallel with main detonation chamber respectively of the second jet pipe, two jet pipe one end are positioned at main detonation chamber, two jet pipe end sidewalls have the first jet pipe outlet and the outlet of the second jet pipe, jet pipe exit opening direction is consistent with airintake direction, the other end of two jet pipes lays respectively in the first pre-explosion pipe and the second pre-explosion pipe, the end sidewalls of two jet pipes has pinking jet conduction hole, the pinking jet conduction hole center of circle and pre-explosion pipe central axis, shock wave focus cavity is positioned at main detonation chamber inner outlet position, is connected by pole and main detonation chamber, and guide ring is positioned at main detonation chamber outlet end, is fixedly connected with main detonation chamber by screw thread, and jet pipe is arranged on guide ring by bolt, described shock wave focus cavity is parabolic type, and cavity wall hoop is evenly equipped with multiple oblique fire discharge orifice, and oblique fire discharge orifice central axis gathers the focus in parabolic type cavity.
2. combined type pulse detonation engine detonation chamber according to claim 1, is characterized in that: the two ends distance that the first jet pipe and the second jet pipe are positioned at main detonation chamber is greater than 1/2 of main detonation chamber radius, but is less than the radius of main detonation chamber.
3. combined type pulse detonation engine detonation chamber according to claim 1, is characterized in that: the first jet pipe outlet is identical with two jet pipe internal diameters with the aperture of the second jet pipe outlet.
4. combined type pulse detonation engine detonation chamber according to claim 1, is characterized in that: the ratio of the cross-section area of shock wave focus cavity and the cross-section area of main detonation chamber is 1/2 ~ 1/3.
5. combined type pulse detonation engine detonation chamber according to claim 1, is characterized in that: the channelization angle of guide ring is greater than 5 degree.
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| CN201410123565.9A CN103899435B (en) | 2014-03-28 | 2014-03-28 | A kind of combined type pulse detonation engine detonation chamber |
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| CN103899435B true CN103899435B (en) | 2015-11-18 |
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Families Citing this family (11)
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| CN104481732B (en) * | 2014-10-19 | 2016-09-28 | 赵晴堂 | The many point sets of array quick-fried formula pulse-knocking engine |
| CN104500272A (en) * | 2014-11-26 | 2015-04-08 | 南京航空航天大学 | Low-flow-resistant near-wall small-space annular shock wave focusing direct priming device |
| CN107605603B (en) * | 2017-08-28 | 2019-02-05 | 江苏大学 | A kind of ignition system for pulse-knocking engine |
| CN109653876B (en) * | 2019-01-14 | 2021-05-11 | 南京航空航天大学 | Short-distance compact ignition initiation device for continuous rotation detonation engine |
| CN109946086B (en) * | 2019-04-09 | 2020-08-25 | 西北工业大学 | Design method of detonation chamber with obstacle for PLIF measurement technology |
| CN110131071B (en) * | 2019-05-04 | 2021-06-15 | 西北工业大学 | Pulse detonation engine combustion chamber and detonation method thereof |
| CN110410231B (en) * | 2019-07-08 | 2020-08-18 | 华中科技大学 | Air-breathing two-stage shock wave focusing ignition engine combustion chamber and working method thereof |
| CN110516310B (en) * | 2019-07-31 | 2022-10-04 | 中国空气动力研究与发展中心 | Unsteady numerical simulation method for rotary detonation back pressure |
| CN112459927A (en) * | 2020-10-23 | 2021-03-09 | 南京理工大学 | Y-shaped small-size bidirectional predetonation ignition tube |
| CN113153569B (en) * | 2021-04-27 | 2022-10-28 | 西北工业大学 | Multi-pipe pulse detonation engine capable of stably exhausting |
| CN114893322A (en) * | 2022-04-08 | 2022-08-12 | 中国人民解放军空军工程大学 | Axial shock wave incident detonation device with a plurality of micro shock tubes uniformly distributed in circumferential direction and operation method |
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| US8429893B2 (en) * | 2009-08-11 | 2013-04-30 | Northrop Grumman Corporation | Airflow modulation for dual mode combined cycle propulsion systems |
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Patent Citations (3)
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|---|---|---|---|---|
| CN101806260A (en) * | 2010-03-04 | 2010-08-18 | 西北工业大学 | Multitube parallel pulse detonation combustion chamber and ignition detonation method thereof |
| CN201858046U (en) * | 2010-11-11 | 2011-06-08 | 西北工业大学 | Pulse detonation engine realizing secondary detonation |
| CN202578943U (en) * | 2012-03-31 | 2012-12-05 | 西北工业大学 | Jet ignition device for pulse detonation engine |
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