CN201614995U - Anti-reverse flow mechanism of suction type pulse detonation engine - Google Patents
Anti-reverse flow mechanism of suction type pulse detonation engine Download PDFInfo
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- CN201614995U CN201614995U CN2010201091537U CN201020109153U CN201614995U CN 201614995 U CN201614995 U CN 201614995U CN 2010201091537 U CN2010201091537 U CN 2010201091537U CN 201020109153 U CN201020109153 U CN 201020109153U CN 201614995 U CN201614995 U CN 201614995U
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Abstract
The utility model provides an anti-reverse flow mechanism of a suction type pulse detonation engine, which comprises a first flange, a pipe section, a bracket, a spring, a valve and a second flange; a projection in the pipe section forms a throat part, a circular through hole is formed in the middle of the throat part, and the through hole shares the same axis with the pipe section; the bracket comprises a circular ring thin sheet and a supporting rod, a cross beam along the diameter of the through hole in the middle of the circular ring is arranged in the through hole, the supporting rod is fixedly connected in the middle of the cross beam and vertically arranged on the circular ring, and the length of the supporting rod is larger than of the axial length of the pipe section; the valve adopts a cone, the diameter of a base plate is identical to that of the through hole at the throat part of the pipe section, and a through hole is axially formed in the middle of the valve; and the two ends of the pipe section are connected with the first and the second flanges respectively, the bracket is connected on one side of the first flange, the spring and the valve are sleeved on the supporting rod, and the base plate of the valve is placed on the outer side of the throat part of the pipe section when the spring is in loose state. The utility model can prevent working media from back conveying so as to produce negative thrust force when the engine is working, and can achieve the function of shock wave reflection so as to convey the blocked working media out from the exhaust cone, thereby enhancing the thrust force.
Description
Technical field
The utility model relates to a kind of anti-reverse-flow mechanism, is specially a kind of air-breathing pulse detonation engine anti-reverse-flow mechanism.
Background technique
For a kind of air-breathing pulse detonation engine, in recent years in the atomizing that has overcome liquid fuel, fast detonate and a difficult problem such as stable operation after, be applied to engineering reality, it is to be solved to also have a prior key issue to have, and that is exactly how to produce significantly effectively positive thrust.Since air-breathing pulse detonation engine by air self-suction as oxygenant; therefore the air-breathing pulse detonation engine front end is an opening; so when engine operation; usually shock wave, flame and the part combustion gas anti-pass that produces in the meeting combuster; opening ejection from motor head; thereby form negative thrust, this makes air-breathing pulse detonation engine be difficult to produce effective positive thrust.The association area researchers have made big quantity research both at home and abroad, design various pneumatic valves, mechanical valve and pneumatic machinery valve etc., but the pertinent literature and the report of the effective positive thrust of rarely seen generation.
The model utility content
The technical problem that solves
In order to prevent air-breathing pulse detonation engine when work, the working medium such as shock wave, flame and part combustion gas that produce in the firing chamber form negative thrust to the engine head anti-pass, and simultaneously unobstructed smoothly for the forward flow that makes flammable mixed gas in the air-breathing pulse detonation engine filling process, the utility model proposes a kind of air-breathing pulse detonation engine anti-reverse-flow mechanism.
Technological scheme
Technical characteristics of the present utility model is:
A kind of air-breathing pulse detonation engine anti-reverse-flow mechanism comprises first flange, pipeline section, support, spring, valve and second flange;
Described pipeline section is the round tubular structure of both ends open, and wherein there is wide inwardly protruding inside, an end opening place, forms the throat of pipeline section; The outside diameter of throat's central through bore is slightly larger than inside diameter; Described support comprises annulus thin slice and pole, on the annulus thin slice attachment hole is arranged, attachment hole is corresponding with attachment hole on first flange, the diameter of annulus thin slice middle part through hole is identical away from the diameter of throat's one end opening with pipeline section, one crossbeam along through-hole diameter is arranged in the through hole, the crossbeam two ends are fixed on the through hole edge, and the crossbeam center is fixedly connected with the pole perpendicular to annulus thin slice cross section, in the pole end stops are arranged; Described valve is a cone, and the diameter on circular cone chassis is identical with the outside diameter of pipeline section throat central through bore, the valve center have along valve shaft to through hole;
Each parts annexation of described air-breathing pulse detonation engine anti-reverse-flow mechanism is: fixedly connected away from an end of throat and the toroidal surface of support with pipeline section respectively in the first flange two ends; The pole of support extend into pipeline section inside, and the central lines of the center line of pole and pipeline section; Spring and valve sleeve are on the pole of support, spring one end is fixedly connected on the crossbeam of support, the other end is fixedly connected on the vertex of a cone end of valve, and valve can be along the pole axial free movement of support, and the valve chassis was in the pipeline section throat outside when spring was in relaxed state; The other end of pipeline section is fixedlyed connected with second flange.
Be circular arc chamfering on the chassis circumference of described valve; Valve cone face is the cambered surface of indent.
Between the through hole both sides of described pipeline section throat is the indent arc transition, and the arc transition face cooperates with circular arc chamfering on the circumference of valve chassis; Pipeline section throat outside body is a straight tube structure, and straight tube and throat are the right angle transition.
The inboard body of described pipeline section throat is a straight tube structure, and straight tube and throat are the cambered surface transition.
The inboard body of described pipeline section throat is bell evagination tapered configuration.
The inboard body of described pipeline section throat is the indent tapered configuration, and pipeline section throat outside body is a straight tube structure, and straight tube and throat are the cambered surface transition.
Beneficial effect
Adopt a kind of air-breathing pulse detonation engine anti-reverse-flow described in the utility model mechanism, in the time of can preventing air-breathing pulse detonation engine work, the working medium such as shock wave, flame and part combustion gas that produce in the firing chamber form negative thrust to the engine head anti-pass, and can make the forward flow of flammable mixed gas in the air-breathing pulse detonation engine filling process unobstructed smoothly simultaneously, and can produce effects such as shock wave reflection, make working medium such as being subjected to shock wave that valve hinders, high-temperature high-pressure fuel gas spread out of, thereby strengthen positive thrust from jet pipe.
Description of drawings
Fig. 1: the utility model structure sectional view (corresponding embodiment 1);
Fig. 2: pipeline section structure sectional view (corresponding embodiment 1);
Fig. 3: rack assumption diagram;
Fig. 4: the utility model structure sectional view (corresponding embodiment 2);
Fig. 5: the utility model structure sectional view (corresponding embodiment 3);
Wherein, 1, first flange; 2, pipeline section; 3, support; 4, spring; 5, valve; 6, second flange.
Embodiment
Now in conjunction with the accompanying drawings the utility model is further described:
Use a kind of air-breathing pulse detonation engine of the present utility model mainly to form, connect with flange between each constituent element by intake duct, mixing chamber, igniting chamber, detonation chamber and jet pipe.
Embodiment 1:
With reference to accompanying drawing 1, a kind of air-breathing pulse detonation engine anti-reverse-flow mechanism comprises first flange 1, pipeline section 2, support 3, spring 4, valve 5 and second flange 6.
With reference to accompanying drawing 2, pipeline section 2 is the round tubular structure of both ends open; At close pipeline section 2 one end opening places, along circumference inwardly protruding perpendicular to pipeline section 2 central axis is arranged, form the throat of pipeline section 2, the throat center is a manhole, through hole two ends diameter is slightly different, near the through hole outer end slightly larger in diameter of second flange 6, and between the two ends of through hole the inner concave arc surface transition, through hole central axis and pipeline section 2 central axes; Body between the throat in the pipeline section 2 and second flange 6 is a straight tube structure, and straight tube and throat are the right angle transition; Body between the throat in the pipeline section 2 and first flange 1 also is a straight tube structure, but straight tube and throat are the cambered surface transition.
With reference to accompanying drawing 3, support 3 is made up of annulus flake structure and pole, and being evenly equipped with 6 on the annulus has attachment hole, and is corresponding with the attachment hole on first flange 1; The diameter of annulus middle part through hole is identical away from the opening diameter of throat's one end with pipeline section 2; In the through hole of annulus middle part, a crossbeam along through-hole diameter is arranged, the crossbeam two ends are fixed on the through hole edge, the crossbeam center is welded with pole, pole is perpendicular to ring cross-section, and strut lengths slightly is longer than the axial length of pipeline section 2, in the pole end stops is arranged, be used to prevent that valve 5 is from upward slippage of pole.
Valve 5 is for having the taper on certain thickness chassis, the chassis is circular, the thickness of projection that forms throat in thickness and the pipeline section 2 is identical, the chassis diameter is identical with the outer end diameter of pipeline section 2 throat's central through bores, on the circumference of chassis circular arc chamfering is arranged, chamfering cooperates with the indent arc transition face at throat central through bore two ends in the pipeline section 2; Valve 5 centers have along valve shaft to through hole, the through hole sectional shape is identical with the sectional shape of support 3 upper rack posts, valve 5 cone faces are the cambered surface of indent, promptly adopt inner concave arc surface as transition from the top of valve 5 cones to the chassis.
Above-mentioned first flange 1, pipeline section 2, support 3, spring 4, valve 5 and second flange, 6 each parts annexation are: first flange, 1 one ends and pipeline section 2 are away from the end welding of throat, and first flange, 1 the other end adopts bolt to be connected with the annulus of support 3 by attachment hole; The pole of support 3 extend into pipeline section 2 inside, and the central lines of the center line of pole and pipeline section 2; Spring 4 and valve 5 are enclosed within on the pole of support 3, spring 4 one ends are welded on the crossbeam of support 3, and the other end is welded on the vertex of a cone end of valve 5, and valve 5 can be along the pole axial free movement of support 3, when spring 4 was in relaxed state, the chassis of valve 5 was in the outside of pipeline section 2 throats; The other end of pipeline section 2 and 6 welding of second flange.
This air-breathing pulse detonation engine anti-reverse-flow mechanism is installed between air-breathing pulse detonation engine mixing chamber and the igniting chamber.When motor was not worked, spring 4 was in relaxed state, the throat portion in the chassis of valve 5 and the pipeline section 2 from.When motor begins to fill, the mixed combustible gas body enters in the pipeline section 2 by first flange 1, because spring 4 elasticity coefficient of using are very little, valve 5 is forward slided under the effect of inflammable mixture stream, distance between valve 5 and pipeline section 2 throats strengthens, make air-flow path become big, fill resistance and reduce rapidly, the forward flow of flammable mixed gas is unobstructed more smoothly.After filling process finishes, the igniting chamber igniting, detonation wave is lighted and formed to flammable mixed gas, this moment the firing chamber in a part of shock wave, working medium such as flame and high-temperature high-pressure fuel gas is to the engine head backpropagation, promptly enter the pipeline section 2 from second flange 6, when passing to valve 5 places, working medium such as the shock wave of anti-pass and high-temperature high-pressure fuel gas promote throat's closure of valve 5 and pipeline section 2 rapidly, thereby thoroughly stoped shock wave, the further anti-pass of working medium such as high-temperature high-pressure fuel gas, thereby eliminated because the negative thrust that anti-pass causes, and because the body between pipeline section 2 throats and second flange 6 is a straight tube, and straight tube and throat are the right angle transition, can produce effects such as shock wave reflection, make this part shock wave, working medium such as high-temperature high-pressure fuel gas can spread out of from jet pipe, thereby strengthen positive thrust.
Embodiment 2:
Present embodiment is that than embodiment's 1 difference throat and the body between first flange 1 in the pipeline section 2 are bell evagination tapered configuration.Straight tube cambered surface transition structure than embodiment 1 adopts this tapered configuration can reduce the flow losses of the flammable mixed gas of filling process.
Embodiment 3:
Present embodiment is that than embodiment 1 difference throat in the pipeline section 2 and the body between first flange 1 are the indent tapered configuration, and the body between pipeline section 2 throats and second flange 6 is a straight tube structure, and straight tube and throat are the cambered surface transition.Bell evagination tapered configuration in the embodiment 2 between the throat and first flange 1 adopts this indent tapered configuration can reduce the negative thrust that the flammable mixed gas gas shock reducing pipe wall of filling process produces; And in embodiment 1 and the embodiment 2 the straight tube right angle transition structure between throat and second flange 6, adopt the straight tube cambered surface transition structure of present embodiment can reduce in the filling process because the flammable mixed gas flow losses that the pipeline sudden expansion produces.
Claims (6)
1. an air-breathing pulse detonation engine anti-reverse-flow mechanism is characterized in that: comprise first flange (1), pipeline section (2), support (3), spring (4), valve (5) and second flange (6);
Described pipeline section (2) is the round tubular structure of both ends open, and wherein there is wide inwardly protruding inside, an end opening place, forms the throat of pipeline section (2); The outside diameter of throat's central through bore is slightly larger than inside diameter; Described support (3) comprises annulus thin slice and pole, on the annulus thin slice attachment hole is arranged, attachment hole is corresponding with attachment hole on first flange (1), the diameter of annulus thin slice middle part through hole is identical away from the diameter of throat's one end opening with pipeline section (2), one crossbeam along through-hole diameter is arranged in the through hole, the crossbeam two ends are fixed on the through hole edge, and the crossbeam center is fixedly connected with the pole perpendicular to annulus thin slice cross section, in the pole end stops are arranged; Described valve (5) is a cone, and the diameter on circular cone chassis is identical with the outside diameter of pipeline section (2) throat central through bore, and valve (5) center has along the axial through hole of valve (5);
Each parts annexation of described air-breathing pulse detonation engine anti-reverse-flow mechanism is: fixedly connected away from an end of throat and the toroidal surface of support (3) with pipeline section (2) respectively in first flange (1) two ends; The pole of support (3) extend into pipeline section (2) inside, and the central lines of the center line of pole and pipeline section (2); Spring (4) and valve (5) are enclosed within on the pole of support (3), spring (4) one ends are fixedly connected on the crossbeam of support (3), the other end is fixedly connected on the vertex of a cone end of valve (5), valve (5) can be along the pole axial free movement of support (3), spring (4) when being in relaxed state valve (5) chassis in pipeline section (2) the throat outside; The other end of pipeline section (2) is fixedlyed connected with second flange (6).
2. a kind of air-breathing pulse detonation engine anti-reverse-flow according to claim 1 mechanism is characterized in that: on the circumference on described valve (5) chassis circular arc chamfering is arranged; Valve (5) cone face is the cambered surface of indent.
3. a kind of air-breathing pulse detonation engine anti-reverse-flow according to claim 1 and 2 mechanism, it is characterized in that: for the indent arc transition, and the arc transition face cooperates with circular arc chamfering on the circumference of valve (5) chassis between the through hole both sides of described pipeline section (2) throat; Pipeline section (2) throat outside body is a straight tube structure, and straight tube and throat are the right angle transition.
4. a kind of air-breathing pulse detonation engine anti-reverse-flow according to claim 3 mechanism, it is characterized in that: the inboard body of pipeline section (2) throat is a straight tube structure, and straight tube and throat are the cambered surface transition.
5. a kind of air-breathing pulse detonation engine anti-reverse-flow according to claim 3 mechanism, it is characterized in that: the inboard body of pipeline section (2) throat is bell evagination tapered configuration.
6. a kind of air-breathing pulse detonation engine anti-reverse-flow according to claim 3 mechanism, it is characterized in that: the inboard body of pipeline section (2) throat is the indent tapered configuration, and pipeline section (2) throat outside body is a straight tube structure, and straight tube and throat are the cambered surface transition.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010201091537U CN201614995U (en) | 2010-02-04 | 2010-02-04 | Anti-reverse flow mechanism of suction type pulse detonation engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010201091537U CN201614995U (en) | 2010-02-04 | 2010-02-04 | Anti-reverse flow mechanism of suction type pulse detonation engine |
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| Publication Number | Publication Date |
|---|---|
| CN201614995U true CN201614995U (en) | 2010-10-27 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2010201091537U Expired - Fee Related CN201614995U (en) | 2010-02-04 | 2010-02-04 | Anti-reverse flow mechanism of suction type pulse detonation engine |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103089445A (en) * | 2013-01-25 | 2013-05-08 | 西北工业大学 | Counter pressure preventing structure of air inlet channel of inspiration type impulse knocking engine |
| CN103133181A (en) * | 2013-02-26 | 2013-06-05 | 西北工业大学 | Fire damper for secondary detonation-breathing pulse detonation engine |
| CN107905915A (en) * | 2017-10-23 | 2018-04-13 | 西北工业大学 | A kind of pulse-knocking engine pressure anti-pass suppresses structure |
| CN109322760A (en) * | 2018-11-07 | 2019-02-12 | 湖南航翔燃气轮机有限公司 | The gas-turbine unit and its fuel combustion method of pulse-combustion mode |
| CN112324587A (en) * | 2021-01-04 | 2021-02-05 | 成都裕鸢航空零部件制造有限公司 | Aircraft engine |
| CN113833569A (en) * | 2021-10-18 | 2021-12-24 | 南京航空航天大学 | Shock wave forward transmission inhibiting structure of isolation section for internal combustion wave rotor and internal combustion wave rotor |
-
2010
- 2010-02-04 CN CN2010201091537U patent/CN201614995U/en not_active Expired - Fee Related
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103089445A (en) * | 2013-01-25 | 2013-05-08 | 西北工业大学 | Counter pressure preventing structure of air inlet channel of inspiration type impulse knocking engine |
| CN103133181A (en) * | 2013-02-26 | 2013-06-05 | 西北工业大学 | Fire damper for secondary detonation-breathing pulse detonation engine |
| CN107905915A (en) * | 2017-10-23 | 2018-04-13 | 西北工业大学 | A kind of pulse-knocking engine pressure anti-pass suppresses structure |
| CN107905915B (en) * | 2017-10-23 | 2019-08-13 | 西北工业大学 | A kind of pulse-knocking engine pressure anti-pass inhibition structure |
| CN109322760A (en) * | 2018-11-07 | 2019-02-12 | 湖南航翔燃气轮机有限公司 | The gas-turbine unit and its fuel combustion method of pulse-combustion mode |
| CN112324587A (en) * | 2021-01-04 | 2021-02-05 | 成都裕鸢航空零部件制造有限公司 | Aircraft engine |
| CN113833569A (en) * | 2021-10-18 | 2021-12-24 | 南京航空航天大学 | Shock wave forward transmission inhibiting structure of isolation section for internal combustion wave rotor and internal combustion wave rotor |
| CN113833569B (en) * | 2021-10-18 | 2022-06-24 | 南京航空航天大学 | Shock wave forward transmission inhibiting structure of isolation section for internal combustion wave rotor and internal combustion wave rotor |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20101027 Termination date: 20130204 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |