CN1472433A - Jet supercharged thrust regulatable impulse detonation engine and method for increasing its thrust - Google Patents
Jet supercharged thrust regulatable impulse detonation engine and method for increasing its thrust Download PDFInfo
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- CN1472433A CN1472433A CNA031460321A CN03146032A CN1472433A CN 1472433 A CN1472433 A CN 1472433A CN A031460321 A CNA031460321 A CN A031460321A CN 03146032 A CN03146032 A CN 03146032A CN 1472433 A CN1472433 A CN 1472433A
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Abstract
A method and apparatus for increasing the propelling force of pulse engine features that the fuel nozzle of pulse explosion engine is arranged in combustion chamber to close jet tube exit, and the fuel is reversely sprayed out to generate a shock wave barrier near the jet tube for preventing the airflow from flowing out of the combustion chamber, resulting in raising the pressure in combustion chamber and in turn increasing the propelling force.
Description
Technical field
The present invention relates to a kind of jet supercharging type thrust controllable pulse detonation engine, and the method that improves pulsed motor thrust, particularly a kind of pulse detonation motor that is used for aerospace field of new ideas.
Background technique
At present, the working pressure of the firing chamber of common Aero-Space turbojet, pressed engine or rocket motor all is normal value.And theory analysis shows, if the detonation process is adopted in the firing chamber, can form an approximate isochoric combustion, and efficiency of engine can increase substantially.So countries in the world are all in research and development " pulse detonation motor " at present.But, after the gas after the isochoric combustion in the firing chamber flows out jet pipe, because the ejector action of combustion gas, internal pressure of combustion chamber is reduced significantly, the combination gas pressure that can make next circulation spray into the firing chamber like this is lower, produces detonation even at this moment ignite combination gas, and the pressure after the detonation just can not be very high, the thrust of detonation engine just can not be very big, and " efficient low energy " phenomenon has appearred in promptly such detonation engine operating mode; In addition, the direct eliminating of detonation wave also causes very high noise.So how improving the pulse detonation motor power, reducing the exhaust sound problem is that the difficult problem that the backroom boys of detonation engine is badly in need of solving is devoted to study in the present whole world.
Summary of the invention
In order to overcome the defective that prior art exists, solve the thrust problem of pulse detonation motor, one of purpose of the present invention is exactly to propose a kind of high thrust pulse detonation motor; Another object of the present invention is to propose a kind of method that can improve the pulse detonation motor power.Since have only improve the indoor mixed gas of pulse detonation engine combustion and ignite before pressure, the pressure after the detonation is improved, and then obtain bigger motor power.So improving the preceding pressure of the indoor mixed gas ignition of pulse detonation engine combustion is the key of dealing with problems.
First purpose of the present invention is achieved in that
A kind of jet supercharging type thrust controllable pulse detonation engine comprises the firing chamber, fuel nozzle, combustion-supporting gas nozzle, jet pipe and firing head five parts.
Second purpose of the present invention is achieved in that
A. the fuel nozzle with the pulse detonation motor is placed on combustor exit near near the jet pipe, and fuel and AIR MIXTURES reverse (that is: in the firing chamber) are sprayed, stop air-flow to flow out the shock wave of firing chamber together near forming near the jet pipe in the firing chamber like this, shock wave is upstream propagated and is made mixture pressure rising in the firing chamber; By regulating the reverse jet intensity of mixture, can regulate the pressurized effect of firing chamber.
B. by the mixed gas in firing head ignition firing chamber, just can obtain stronger detonation wave, internal pressure of combustion chamber be improved rapidly, and then obtain bigger thrust; In addition, because firing head is placed on combustor exit near the jet pipe place, detonation wave will upstream be propagated like this, and gas is got rid of downstream behind the ripple, can reduce noise.
Can obtain mixture pressure before the higher indoor ignition of pulse detonation engine combustion according to method of the present invention, thereby strengthened the pressure after the detonation in the firing chamber, and then obtain than high thrust, solve present detonation engine " efficient low energy " this difficult problem and reduced exhaust sound.Simultaneously because structure of the present invention is simple especially, so realize being very easy to.
Description of drawings
Fig. 1 is a jet supercharging type thrust controllable pulse engine combustion chamber structure schematic representation of the present invention.
Embodiment
Further specify the present invention and working procedure thereof below in conjunction with accompanying drawing.
Jet supercharging type thrust controllable pulse detonation engine of the present invention comprises firing chamber 1, fuel air mixture nozzle 2, combustion-supporting gas nozzle 3, jet pipe 4, firing head 5; Fuel and air mixture nozzle 2 places near the 1 outlet jet pipe 4 of firing chamber; Firing head 5 is placed in the firing chamber 1 near near the jet pipe 4; Fuel and air mixture nozzle 2 reverse (in the firing chamber) ejection fuel and air mixture.
During work, when the mixture pressure in the detonation engine firing chamber reaches design load, close fuel nozzle and combustion-supporting gas nozzle, and firing head is ignited mixed gas and make it that detonation take place, because the detonation velocity of wave propagation is very fast, so nearly isochoric combustion process has taken place in the firing chamber, pressure in the firing chamber after the detonation is directly proportional with mixture pressure before its detonation, because the pressure in the firing chamber is far above external pressure at this moment, the gas of burning is sprayed backward by jet pipe, and motor produces thrust forward.The thrust of motor is the increasing function of the pressure of this moment in the firing chamber, that is: internal pressure of combustion chamber is high more, and thrust is just big more.After the gas after the burning flows to end, open fuel nozzle and combustion-supporting gas nozzle, in the firing chamber, inject mixed gas again, next circulation beginning.But because the ejector action of gas behind the last circulating combustion, the pressure in the firing chamber can be very low.As shown in Figure 1, the present invention is seated in firing chamber 1 near near the jet pipe 4 with fuel and AIR MIXTURES nozzle 2, and the mixture reverse (that is: in the firing chamber) of fuel mixture nozzle ejection is sprayed, in the firing chamber, stop air-flow to flow out the shock wave of firing chamber together like this near forming near the jet pipe, the effect of shock wave is that internal pressure of combustion chamber is raise, have only internal pressure of combustion chamber to raise, could obtain stronger detonation wave by the mixed gas that firing head 5 is ignited in the firing chamber, internal pressure of combustion chamber is improved rapidly, thereby obtain bigger thrust.
Claims (4)
1, a kind of jet supercharging type thrust controllable pulse detonation engine, comprise firing chamber (1), fuel and air mixture nozzle (2), combustion-supporting gas nozzle (3), jet pipe (4), firing head (5), it is characterized in that described fuel and air mixture nozzle (2) places near firing chamber (1) the outlet jet pipe (4).
2, as right 1 described jet supercharging type thrust controllable pulse detonation engine, it is characterized in that described fuel and air mixture nozzle (2) reverse (in the firing chamber) ejection fuel and air mixture.
As jet supercharging type thrust controllable pulse detonation engine as described in the right 1,2, it is characterized in that 3, described firing head (5) is placed in the firing chamber (1) near near the jet pipe (4).
4, a kind of method that improves the pulse detonation motor power is characterized in that,
A. the fuel nozzle with the pulse detonation motor is placed on combustor exit near near the jet pipe, and fuel and AIR MIXTURES reverse (that is: in the firing chamber) are sprayed, stop air-flow to flow out the shock wave of firing chamber together near forming near the jet pipe in the firing chamber like this, shock wave is upstream propagated and is made mixture pressure rising in the firing chamber; By regulating the reverse jet intensity of mixture, can regulate the pressurized effect of firing chamber;
B. by the mixed gas in firing head ignition firing chamber, just can obtain stronger detonation wave, internal pressure of combustion chamber be improved rapidly, and then obtain bigger thrust; In addition, because firing head is placed on combustor exit near the jet pipe place, detonation wave will upstream be propagated like this, and gas is got rid of downstream behind the ripple, can reduce noise.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB031460321A CN1173113C (en) | 2003-07-14 | 2003-07-14 | Jet supercharged thrust regulatable impulse detonation engine and method for increasing its thrust |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB031460321A CN1173113C (en) | 2003-07-14 | 2003-07-14 | Jet supercharged thrust regulatable impulse detonation engine and method for increasing its thrust |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN1472433A true CN1472433A (en) | 2004-02-04 |
| CN1173113C CN1173113C (en) | 2004-10-27 |
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| Application Number | Title | Priority Date | Filing Date |
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| CNB031460321A Expired - Fee Related CN1173113C (en) | 2003-07-14 | 2003-07-14 | Jet supercharged thrust regulatable impulse detonation engine and method for increasing its thrust |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101858278A (en) * | 2010-05-06 | 2010-10-13 | 上海大学 | Multi-tube detonation lateral wave ignition device |
| WO2011113306A1 (en) * | 2010-03-15 | 2011-09-22 | Jin Beibiao | Gas piston pulse engine |
| CN108170961A (en) * | 2017-12-29 | 2018-06-15 | 中国航天空气动力技术研究院 | A kind of method for improving rotation detonation engine fuel oxidant blending efficiency |
| CN110220942A (en) * | 2019-06-10 | 2019-09-10 | 上海交通大学 | A kind of detonation excitation system and method based on high-speed jet |
| CN111894762A (en) * | 2020-07-08 | 2020-11-06 | 南京理工大学 | Transient detonation pulse engine and radial multi-pulse thrust vector device |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101825041B (en) * | 2010-03-15 | 2013-06-05 | 靳北彪 | Gas piston pulse engine |
-
2003
- 2003-07-14 CN CNB031460321A patent/CN1173113C/en not_active Expired - Fee Related
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2011113306A1 (en) * | 2010-03-15 | 2011-09-22 | Jin Beibiao | Gas piston pulse engine |
| CN101858278A (en) * | 2010-05-06 | 2010-10-13 | 上海大学 | Multi-tube detonation lateral wave ignition device |
| CN101858278B (en) * | 2010-05-06 | 2012-08-29 | 上海大学 | Multi-tube detonation lateral wave ignition device |
| CN108170961A (en) * | 2017-12-29 | 2018-06-15 | 中国航天空气动力技术研究院 | A kind of method for improving rotation detonation engine fuel oxidant blending efficiency |
| CN110220942A (en) * | 2019-06-10 | 2019-09-10 | 上海交通大学 | A kind of detonation excitation system and method based on high-speed jet |
| CN111894762A (en) * | 2020-07-08 | 2020-11-06 | 南京理工大学 | Transient detonation pulse engine and radial multi-pulse thrust vector device |
| CN111894762B (en) * | 2020-07-08 | 2021-09-21 | 南京理工大学 | Transient detonation pulse engine and radial multi-pulse thrust vector device |
Also Published As
| Publication number | Publication date |
|---|---|
| CN1173113C (en) | 2004-10-27 |
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