CN102619643B - Jet ignition device of pulse detonation engine - Google Patents
Jet ignition device of pulse detonation engine Download PDFInfo
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- CN102619643B CN102619643B CN2012100927795A CN201210092779A CN102619643B CN 102619643 B CN102619643 B CN 102619643B CN 2012100927795 A CN2012100927795 A CN 2012100927795A CN 201210092779 A CN201210092779 A CN 201210092779A CN 102619643 B CN102619643 B CN 102619643B
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Abstract
The invention relates to a jet ignition device of a pulse detonation engine, which is characterized in that a jet tube is fixedly connected with a mixing chamber through a sealing clamp nut, an adjusting plug is mounted at the top end of the jet tube through a sealing nut and a clamping nut; a drain tube is arranged in a jet chamber inside the jet tube and is connected with the jet tube through a fixing rib, and the lower end of the drain tube extends into the mixing chamber; and an ignition seat is arranged on one side of the jet tube and is located at one end of an outlet of the drain tube. Compared with the time and the distance for generating detonation waves by normal ignition devices, the time and the distance for generating the detonation waves by the jet ignition device are shorter, accordingly the DDT (deflagration to detonation transition) time and distance is shortened. In this case, length of a detonation chamber can be further shortened so as to improve working frequency of the pulse detonation engine. After the detonation chamber is shortened, exhausting burden in the pulse detonation engine is reduced, so that expansion wave-beams generated from the outlet of the pulse detonation engine can catch up with pressure waves transmitted before, pressure disturbance in an air-inlet passage is reduced, and working stability of the pulse detonation engine is enhanced while better propulsive performance is achieved.
Description
Technical field
The present invention relates to technical field of engines, relate in particular to a kind of pulse-knocking engine jet initiation device.
Background technique
Pulse-knocking engine is a kind of high temperature that utilizes intermittent detonation wave to produce, the new concept propulsion device that high-pressure gas produces thrust.According to whether carrying oxygenant, pulse-knocking engine is divided into air-breathing pulse detonation engine and rocket type pulse-knocking engine.
Need huge ignition energy owing to directly triggering pinking, from practicability, the general employing of pulse-knocking engine igniting weak spark igniting and pre-explosion pipe igniting.The former changes (DDT) by the optimal design to seed region and detonation to pinking and realizes knocking combustion.The latter is generally by lighting the mixture in pre-explosion pipe, and combustion gas enters main combustion chamber and lights the mixed gas of main combustion chamber.Although weak spark igniting form is simple, because ignition energy is little, need the DDT distance of a section longer.Longer DDT, apart from the raising of meeting limiting engine frequency, is unfavorable for improving engine performance.Although pre-explosion pipe igniting ignition energy is larger, can reduce the DDT distance, but this firing mode needs a pre-explosion pipe to ignite main detonation tube, pre-explosion pipe needs a set of extra oil gas to supply with and ignition system, increase the complexity of system, also can bring the work matching problem of pre-explosion pipe and main booster simultaneously.
Summary of the invention
The technical problem solved
For fear of the deficiencies in the prior art part, the present invention proposes a kind of pulse-knocking engine jet initiation device, can under the prerequisite of little energy igniting, improve the ignition energy of main booster, thereby shorten DDT distance and time, improve the engine operation frequency, and then promote engine performance.For air-breathing pulse detonation engine, owing to having shortened the DDT time, in a work cycle, motor has the more time for exhaust, thereby reduce the stagnation pressure of anti-pass combustion gas, make the pressure pulsation in intake duct reduce, thereby promote the propulsive performance of air-breathing pulse detonation engine.
Technological scheme
A kind of pulse-knocking engine jet initiation device, is characterized in that comprising mixing chamber 1, drainage tube 2, igniting seat 3, jet pipe 5, igniter 6 and regulate plug 9; Jet pipe 5 is fixedly connected with mixing chamber 1 by sealing tightening nut 4, regulates plug 9 and is installed on jet pipe 5 tops by sealing nut 7 and tightening nut 8; Drainage tube 2 is placed in the jet chamber 10 in jet pipe 5, by fixing rib 11, with jet pipe, is connected, and in lower end extension and mixing chamber 1; Igniting seat 3 is placed in a side of jet pipe 5, and is positioned at outlet one end of drainage tube 2; Flammable mixed gas in mixing chamber 1, a part flows into jet chambeies 10 via drainage tube 2, another part directly enters jet chamber 10, mixed gas phase that these two-part are flammable meet after in jet chamber 10 interior formation low-speed region; Now by igniter 6, light flammable mixed gas, the burning wave and flame is at the interior development in jet chamber 10, and intensity enhancing forms after one thermojet and pours detonation chamber and light flammable mixed gas in detonation chamber and finally form pinking.
The angle of described jet pipe and mixing chamber is 30 °-150 °.
The ratio of described drainage tube internal diameter and jet pipe internal diameter is 0.25-0.5.
Beneficial effect
A kind of pulse-knocking engine jet initiation device that the present invention proposes, beneficial effect is: in general, weak spark is lighted a fire because ignition energy is very little, DDT time and distance that need to be longer.The further raising of this meeting limiting engine frequency of okperation, also just limited the further lifting of the propulsive performance of motor.For air-breathing pulse detonation engine, longer DDT time and distance, except above-mentioned impact is arranged, also can make its intake duct larger pressure pulsation occur, further affect engine operation stability.This is because there is the problem of pressure forward pass in air-breathing pulse detonation engine, and longer DDT distance need to be longer period of exhaust, after detonation wave spreads out of detonation chamber, the expansion wave beam that the motor afterbody produces has little time to catch up with the pressure wave of forward pass and weakens its pressure, makes the anti-pass combustion gas import intake duct into always.The present invention can effectively improve the problems referred to above.The weak spark igniting has simple and easy to do characteristics, and the present invention has still inherited this advantage, but has amplified ignition energy on the basis that adopts the weak spark igniting.Flammable mixed gas is by after being lighted in jet pipe, and the combustion wave development, when flame spreads out of jet pipe and enters detonation chamber, be equivalent to one thermojet and remove to light the flammable mixed gas in detonation chamber.The energy that the common igniting of the energy Ratios of this strand of thermojet discharges is obviously much bigger.So, than common igniting, detonation wave can, in shorter time and the interior generation of distance, namely shorten DDT time and distance.Like this, the length of detonation chamber can further shorten, thereby improves the frequency of okperation of motor.In addition, for air-breathing pulse detonation engine, as mentioned above, after having shortened detonation chamber, in-engine exhaust burden reduces, the expansion wave beam that makes engine export produce can be caught up with the pressure wave of forward pass quickly, reduces the pressure disturbance in intake duct, when promoting engine operation stability, obtains better propulsive performance.
The accompanying drawing explanation
Fig. 1: structural drawing of the present invention;
Fig. 2: Application Example schematic diagram of the present invention;
The 1-mixing chamber, the 2-drainage tube, 3-light a fire the seat, 4-seals tightening nut, 5-jet pipe, 6-igniter, the 7-sealing nut, the 8-tightening nut, 9-regulates plug, 10-jet chamber, 11-fixing rib, 12-cylindrical structural, 13-intake duct wall, 14-inlet cone, 15-fuel nozzle, 16-pinking stiffening device, the 17-detonation chamber.
Embodiment
Now in conjunction with the embodiments, the invention will be further described for accompanying drawing:
The present embodiment comprises mixing chamber 1, drainage tube 2, igniting seat 3, jet pipe 5, igniter 6 and regulates plug 9; Jet pipe 5 is fixedly connected with mixing chamber 1 by sealing tightening nut 4, and jet pipe 5 is 90 ° with the setting angle of mixing chamber 1; Regulate plug 9 and be installed on jet pipe 5 tops by sealing nut 7 and tightening nut 8; Drainage tube 2 is placed in the jet chamber 10 in jet pipe 5, by fixing rib 11, with jet pipe, be connected, and, in lower end extension and mixing chamber 1, the ratio of drainage tube internal diameter and jet pipe internal diameter is 0.3; Igniting seat 3 is placed in a side of jet pipe 5, and is positioned at outlet one end of drainage tube 2; Flammable mixed gas in mixing chamber 1, a part flows into jet chambeies 10 via drainage tube 2, another part directly enters jet chamber 10, mixed gas phase that these two-part are flammable meet after in jet chamber 10 interior formation low-speed region; Now by igniter 6, light flammable mixed gas, the burning wave and flame is at the interior development in jet chamber 10, and intensity enhancing forms after one thermojet and pours detonation chamber and light flammable mixed gas in detonation chamber and finally form pinking.
In the present invention, the volume of jet pipe can be regulated by regulating plug; The setting angle of jet pipe and mixing chamber is not limit, and when the motor radial dimension is restricted, can reduce by the angle of regulating jet pipe and mixing chamber the integrated radial size of motor.
The present embodiment can be used for the pulse-knocking engine igniting chamber, also is applicable to the burner that some requires to improve ignition energy, as aeroengine, rocket motor etc.
As shown in Figures 1 and 2, the present invention includes mixing chamber 1, drainage tube 2, igniting seat 3, sealing tightening nut 4, jet pipe 5, igniter 6, sealing nut 7, tightening nut 8, regulate plug 9, jet chamber 10, fixing rib 11.Intake duct wall 13 forms the intake duct of ring, and air flows into motor by intake duct, and there is an inlet cone 14 at intake duct axis place, and the cylindrical structural 12 at inlet cone rear portion forms an annular pass with intake duct wall 13.Air-flow enters mixing chamber 1 behind annular pass.Fuel oil is by fuel nozzle 15 ejections.After the fuel oil ejection, with air-flow, at mixing chamber 1, mix.A flammable mixed gas part is entered the jet chamber 10 of jet pipe 5 by drainage tube 2, a part directly enters jet chamber 10 by mixing chamber 1 and the connecting passage of jet pipe 5.After two bursts of combustion gas are met, by igniter 6, light mixed gas.After flammable mixed gas is lighted, flame develops in the jet chamber, and its intensity is constantly strengthened, and finally forms one thermojet and pours detonation chamber 17.This strand of thermojet then lighted other flammable mixed gas that are filled in detonation chamber 17, finally forms pinking.
As shown in Figure 2, at pulse-knocking engine, in operation cycle, at first, the incoming flow with certain speed enters intake duct, enters annular pass after walking around inlet cone 14, then enters mixing chamber 1.Fuel oil is by fuel nozzle 15 ejections simultaneously.Blending wellatomized mixed gas are filled detonation chamber 17 with certain speed.Wherein the mixed gas of a part directly enters jet chamber 10. by the connecting passage of drainage tube 2 and mixing chamber 1 and jet pipe 5 respectively and is about to fill complete when detonation chamber 17, igniter 6 is sent to fire signal, igniter 6 light in jet chamber 10 can quick-fried mixture, form detonation.The deflagration wave pressure and temperature constantly raises, and makes flame acceleration, forms one thermojet.Thermojet is then gone out jet chamber 10 and is entered detonation chamber 17 and light the flammable mixed gas in detonation chamber 17.Thermojet intensity after pinking intensifier 16 is strengthened gradually, finally develops into stable detonation wave.
Claims (3)
1. a pulse-knocking engine jet initiation device, is characterized in that comprising mixing chamber (1), drainage tube (2), igniting seat (3), jet pipe (5), igniter (6) and regulate plug (9); Jet pipe (5) is fixedly connected with mixing chamber (1) by sealing tightening nut (4), regulates plug (9) and is installed on jet pipe (5) top by sealing nut (7) and tightening nut (8); Drainage tube (2) is placed in the jet chamber (10) in jet pipe (5), by fixing rib (11), with jet pipe, is connected, and in lower end extension and mixing chamber (1); Igniting seat (3) is placed in a side of jet pipe (5), and is positioned at outlet one end of drainage tube (2); Flammable mixed gas in mixing chamber (1), a part flows into jet chamber (10) via drainage tube (2), and another part directly enters jet chamber (10), and mixed gas phase that these two-part are flammable forms low-speed region after meeting in jet chamber (10); Now by igniter (6), light flammable mixed gas, burning wave and flame development jet chamber (10) in, intensity enhancing, form after one thermojet and pour detonation chamber and light flammable mixed gas the final formation pinking in detonation chamber.
2. pulse-knocking engine jet initiation device according to claim 1, it is characterized in that: the angle of described jet pipe and mixing chamber is 30 °-150 °.
3. pulse-knocking engine jet initiation device according to claim 1, it is characterized in that: the ratio of described drainage tube internal diameter and jet pipe internal diameter is 0.25-0.5.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012100927795A CN102619643B (en) | 2012-03-31 | 2012-03-31 | Jet ignition device of pulse detonation engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012100927795A CN102619643B (en) | 2012-03-31 | 2012-03-31 | Jet ignition device of pulse detonation engine |
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| Publication Number | Publication Date |
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| CN102619643A CN102619643A (en) | 2012-08-01 |
| CN102619643B true CN102619643B (en) | 2013-12-04 |
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| CN2012100927795A Expired - Fee Related CN102619643B (en) | 2012-03-31 | 2012-03-31 | Jet ignition device of pulse detonation engine |
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Families Citing this family (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103835837B (en) * | 2014-03-07 | 2016-01-13 | 南京航空航天大学 | A kind of thermojet generating means based on eddy flow blending and vaporized fuel sustained combustion |
| CN104265506B (en) * | 2014-09-16 | 2016-04-27 | 清华大学 | Pulse-knocking engine |
| CN104612821B (en) * | 2015-01-28 | 2017-01-11 | 南京理工大学 | One-way priming device of probing type rotation detonation engine |
| CN106338083B (en) * | 2016-09-06 | 2019-04-05 | 西北工业大学 | A kind of minute yardstick knock system of variable boundary condition |
| CN106768614A (en) * | 2016-12-08 | 2017-05-31 | 中国人民解放军国防科学技术大学 | A kind of thermojet detonating combustion experimental rig for supersonic speed detonation engine |
| CN107605603B (en) * | 2017-08-28 | 2019-02-05 | 江苏大学 | A kind of ignition system for pulse-knocking engine |
| CN110131071B (en) * | 2019-05-04 | 2021-06-15 | 西北工业大学 | Pulse detonation engine combustion chamber and detonation method thereof |
| CN113153569B (en) * | 2021-04-27 | 2022-10-28 | 西北工业大学 | Multi-pipe pulse detonation engine capable of stably exhausting |
| CN113203103B (en) * | 2021-05-06 | 2022-03-29 | 中国航发湖南动力机械研究所 | Pulse detonation combustion chamber head with precombustion chamber structure |
| CN113310069B (en) * | 2021-06-02 | 2022-03-08 | 常熟理工学院 | Jet ignition device for pulse detonation engine |
| CN113777215B (en) * | 2021-09-26 | 2023-08-25 | 西安航天动力研究所 | Test device for jet flow booster research |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| JPH0633672Y2 (en) * | 1988-07-06 | 1994-08-31 | 日本特殊陶業株式会社 | Cryogenic liquid hydrogen / liquid oxygen fuel igniter plug |
| US7546739B2 (en) * | 2005-07-05 | 2009-06-16 | General Electric Company | Igniter tube and method of assembling same |
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Patent Citations (4)
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|---|---|---|---|---|
| US3651644A (en) * | 1969-06-25 | 1972-03-28 | Marshall Ind | Apparatus for initiating decomposition of an exothermic propellant |
| CN88102194A (en) * | 1987-04-22 | 1988-12-21 | 韦伯斯托汽车公司 | Vaporizing combustor |
| US5109699A (en) * | 1991-06-10 | 1992-05-05 | Husco International | Sonic casting tester |
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| CN102619643A (en) | 2012-08-01 |
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