CN202578942U - Detonation chamber for pulse detonation engine - Google Patents
Detonation chamber for pulse detonation engine Download PDFInfo
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- CN202578942U CN202578942U CN 201220132764 CN201220132764U CN202578942U CN 202578942 U CN202578942 U CN 202578942U CN 201220132764 CN201220132764 CN 201220132764 CN 201220132764 U CN201220132764 U CN 201220132764U CN 202578942 U CN202578942 U CN 202578942U
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Abstract
The utility model relates to a detonation chamber for a pulse detonation engine. The detonation chamber is characterized in that a plurality of detonation enhancement devices are arranged on an inner wall of an engine, wherein an inner diameter which is 0.5 to 1 time that of the thickness of the inner wall of the engine is formed between the detonation enhancement devices at intervals; each detonation enhancement device comprises a shrinkage section, fixing ribs and a drainage section; the shrinkage section for gradually shrinking a runner is formed along the air inlet direction and is connected with the drainage section. Compared with that in the common Schelkin spiral abrupt change runner, the detonation chamber has the advantages that the positive flow loss is low, the positive flow resistance loss in the detonation chamber is reduced, and detonation waves can be formed in a short distance. The detonation enhancement devices are difficult to ablate, and the service life of the detonation chamber can be effectively prolonged. The traditional Schelkin spiral is connected with the engine through a welding mode, when the engine works at high frequency, the temperature in the detonation chamber is extremely high, and the welding spots are easily ablated, so that the Schelkin spiral is ineffective.
Description
Technical field
The present invention relates to technical field of engines, relate in particular to a kind of pulse-knocking engine detonation chamber.
Background technique
Pulse-knocking engine is a kind of high temperature that utilizes intermittent detonation wave to produce, the new ideas advancing means that high-pressure gas produces thrust.According to whether carrying oxygenant, pulse-knocking engine can be divided into two kinds of rocket type and air-inlet types.
The detonation mode of pinking is divided into two kinds, i.e. direct initiation and detonating indirectly.The former needs huge ignition energy, and the latter changes (DDT) through detonation to pinking and forms detonation wave.Consider practicability, the mode that the general employing of pulse-knocking engine is detonated indirectly obtains detonation wave.Specifically, adopt less ignition energy to form the deflagration ripple earlier, finally form detonation wave through flame and the interaction of compressional wave in detonation chamber then.In the pinking transforming process, generally in detonation chamber, arrange obstacle (pinking intensifier) in detonation, strengthen the accelerating process of flame, reduce the DDT distance.The pinking intensifier mainly comprises Schelkin helix structure, baffle arrangement, inner trough structure and other composite structures etc.More common pinking intensifier is the Schelkin spiral at present.Flame is spiral propagating accelerated through uniqueness.This accelerating process has shortened the axial distance of DDT, thereby shortens detonation chamber length.But there is the bigger and easy ablation two large problems of flow resistance loss in the Schelkin spiral.Flow resistance loss makes more greatly and the thrust decreased performance of motor makes engine operational life limited and ablate easily.Because the temperature in the detonation chamber is very high, the ablation problem of Schelkin spiral is particularly serious during high-frequency work.And long-time high-frequency work is the inevitable requirement of pulse-knocking engine practical applications.
For air-breathing pulse detonation engine; In the work cycle, before detonation wave forms, can produce the HTHP point (cross and drive pinking) of some parts in the detonation chamber; Then form stable detonation wave and propagate to outlet, local simultaneously high pressure impels the part combustion gas to propagate to intake duct.The anti-pass combustion gas not only makes the motor propulsive performance descend, and also can influence the proper functioning of motor, and intake duct can not start when serious.The measure of taking to reducing the intake duct back-pressure is at present all carried out in intake duct mostly, like pneumatic valve and mechanical valve etc.Though common detonation chamber can reduce the stagnation pressure of anti-pass combustion gas to a certain extent, it does not consider that it reduces the function of anti-pass gaseous-pressure, so effect and not obvious.(like igniting chamber or detonation chamber) adds the structure reduce back-pressure and also do not see disclosed report at present after intake duct.In fact, the position that the passback detonation wave forms is far away apart from intake duct, in detonation chamber, can implant more effective structure or takes appropriate measures, and under the prerequisite that is not influencing engine operation stability, reduces the pressure of anti-pass combustion gas.
Summary of the invention
The technical problem that solves
Deficiency for fear of existing technology; The present invention proposes a kind of pulse-knocking engine detonation chamber, improves that detonation chamber flow resistance loss under the existing technology is ablated more greatly, easily and the air-breathing pulse detonation engine detonation chamber can not effectively reduce the problem of anti-pass gaseous-pressure.The present invention ground detonation chamber forward flow resistance loss is less, being difficult for ablating also can effectively reduce air-breathing pulse detonation engine anti-pass gaseous-pressure.
Technological scheme
A kind of detonation chamber of pulse-knocking engine is characterized in that: be provided with a plurality of pinking intensifiers at engine inner wall, the internal diameter of 0.5～1 times of engine inner wall of being separated by between each pinking intensifier; Said pinking intensifier comprises contraction section 1, fixing rib 2 and Drainage Section 3; Be provided with one along airintake direction and form the contraction section of contracted channel gradually, be connected a Drainage Section then; The throat area of said Drainage Section is identical with the contraction section throat area; The leading edge of Drainage Section 3 is shunk along the direction of contraction section 1 contracted channel gradually; Form one section straight section parallel on the other hand backward, form a uniform section ring runner with engine inner wall 5 with engine inner wall 5; Drainage Section 3 links to each other with engine inner wall 5 through fixing rib 2, has circular groove between the fin vertically.
The throat diameter of said contraction section and motor internal diameter ratio are not less than 0.65, and the curved surface that contraction section forms is recessed to the detonation chamber medial axis.
The distance of the structure of said contraction section and Drainage Section formation contracted channel is less than 0.15 times of detonation chamber internal diameter.
Said Drainage Section straight section and motor wall are apart less than 0.15 times of detonation chamber internal diameter.
Beneficial effect
A kind of pulse-knocking engine detonation chamber that the present invention proposes, beneficial effect comprises three aspects: at first, because contraction section is a runner that shrinks gradually, than the runner of common Schelkin spiral sudden change, forward flow loss of the present invention is little.Simultaneously detonation chamber inwall of the present invention is not covered with the pinking intensifier fully, is covered with the structure of detonation chamber than common Schelkin spiral, and the present invention has further reduced the forward flow resistance loss in the detonation chamber.And less forward flow resistance loss helps the lifting of motor propulsive performance.But when reducing the forward flow resistance loss, the present invention also can form detonation wave simultaneously in short distance.This be because, be similar to other pinking intensifiers, compressional wave can be between two pinking intensifiers of this detonation chamber repeatedly reflection stack.The repeatedly reflection enhancement of pressure wave the interaction of flame, make flame constantly quicken and the final detonation wave that forms.Secondly, than traditional Schelkin spiral, pinking intensifier of the present invention is difficult for ablating the working life that can improve detonation chamber effectively.Traditional Schelkin spiral is connected with motor through welding manner, and when the motor high-frequency work, the pinking room temperature is very high, and the solder joint of ablating easily makes the Schelkin spiral lose efficacy.
Pinking intensifier of the present invention and motor wall combine together, have enough intensity just not have above-mentioned Problem of Failure as long as guarantee the fixing rib that the Drainage Section is connected with engine inner wall.Once more, for air-breathing pulse detonation engine, some runner of the anti-pass combustion gas meeting in the detonation chamber through each pinking intensifier formation, flow direction deflection has a component velocity backward greater than 90 °.This component velocity backward makes combustion gas change flow direction, has reduced to import into the anti-pass combustion gas quantity in the intake duct.Simultaneously also delayed the time that high-pressure gas imports intake duct into, the expansion wave beam that makes engine export form has the pressure of more time anti-pass combustion gas.In addition, because this structure inner flow passage is complicated, anti-pass gas flow pressure loss after this structure is bigger, and stagnation pressure reduces, and also makes its influence to intake duct weaken.
Description of drawings
Fig. 1: structural drawing of the present invention;
Fig. 2: embodiments of the invention schematic representation;
1. contraction sections among the figure, 2. fixing rib, 3. Drainage Section, 4. detonation chamber, 5. engine inner wall, 6. spark plug, 7. cylindrical structural, 8. inlet cone, 9. fuel nozzle.
Embodiment
Combine embodiment, accompanying drawing that the present invention is further described at present:
Application of the present invention is a pulse-knocking engine detonation chamber as shown in Figure 1.But the present invention is applicable to that also some requires to form burner detonation wave and that reduce to return gaseous-pressure.
Present embodiment is as shown in Figure 2: be provided with 5 pinking intensifiers at the pulse-knocking engine inwall, the internal diameter of the 0.8 times of engine inner wall of being separated by between each pinking intensifier; Said pinking intensifier comprises contraction section 1, fixing rib 2 and Drainage Section 3; Be provided with one along airintake direction and form the contraction section of contracted channel gradually, be connected a Drainage Section then; The throat area of said Drainage Section is identical with the contraction section throat area; The leading edge of Drainage Section 3 is shunk along the direction of contraction section 1 contracted channel gradually; Form one section straight section parallel on the other hand backward, form a uniform section ring runner with engine inner wall 5 with engine inner wall 5; Drainage Section 3 links to each other with engine inner wall 5 through fixing rib 2, has circular groove between the fin vertically.
The throat diameter of said contraction section and motor internal diameter ratio are 0.65, and the curved surface that contraction section forms is recessed to the detonation chamber medial axis.The distance that said contraction section and Drainage Section form the structure of contracted channel is 0.14 times of detonation chamber internal diameter.Said Drainage Section straight section and motor wall apart are 0.14 times of detonation chamber internal diameter.
The working principle of pinking intensifier: the intake duct housing forms the intake duct of ring, and air flows into motor by intake duct, and there is an inlet cone 8 at intake duct axis place, and the cylindrical structural 7 and the intake duct housing at inlet cone rear portion form an annular pass.Air-flow gets into detonation chamber 4 behind the annular pass.Fuel oil is by fuel nozzle 9 ejections.Mix at detonation chamber 4 with air-flow fuel oil ejection back, after both mix, is lighted mixed gas and finally formed pinking by spark plug 6.
The working principle of pulse-knocking engine is as shown in Figure 2, in operation cycle, at first, has the intake duct that flows into of certain speed at pulse-knocking engine, walks around inlet cone 7 backs and gets into annular passs, then gets into detonation chamber 4.Fuel oil is by fuel nozzle 9 ejections simultaneously.Blending and wellatomized mixed gas are filled detonation chamber 4 with certain speed.When detonation chamber 4 fillings finish, igniter 6 is sent fire signal, igniter 6 is lighted and can be formed detonation by quick-fried mixture.The deflagration wave pressure and temperature constantly raises, and flame is quickened.Intensity is strengthened gradually behind the deflagration wave process pinking intensifier, forms a lot of HTHP points in the part.These HTHP points develop into stable detonation wave backward and propagate to the detonation chamber outlet.Impel a part of combustion gas to propagate forward simultaneously.After the anti-pass combustion gas arrived Drainage Section 3, a part of combustion gas got into the runner that Drainage Section 3, engine inner wall 5 and contraction section 1 are formed.Flow direction deflection had a component velocity backward greater than 90 ° after this runner was flowed out in this part combustion gas.This component velocity backward makes combustion gas change flow direction, has reduced to import into the anti-pass combustion gas quantity in the intake duct.Simultaneously also delayed the time that high-pressure gas imports intake duct into, the expansion wave beam that makes engine export form has more time to slacken the pressure of this part combustion gas.In addition, because this structure inner flow passage is complicated, anti-pass gas flow pressure loss after this structure is bigger, and stagnation pressure reduces, and also makes its influence to intake duct weaken.
Claims (4)
1. the detonation chamber of a pulse-knocking engine is characterized in that: be provided with a plurality of pinking intensifiers at engine inner wall, the internal diameter of 0.5～1 times of engine inner wall of being separated by between each pinking intensifier; Said pinking intensifier comprises contraction section (1), fixing rib (2) and Drainage Section (3); Be provided with one along airintake direction and form the contraction section of contracted channel gradually, be connected a Drainage Section then; The throat area of said Drainage Section is identical with the contraction section throat area; The leading edge of Drainage Section (3) is shunk along the direction of contraction section (1) contracted channel gradually; Form backward on the other hand one section with the parallel straight section of engine inner wall (5), form a uniform section ring runner with engine inner wall (5); Drainage Section (3) links to each other with engine inner wall (5) through fixing rib (2), has circular groove between the fin vertically.
2. the detonation chamber of pulse-knocking engine according to claim 1, it is characterized in that: the throat diameter of said contraction section and motor internal diameter ratio are not less than 0.65, and the curved surface that contraction section forms is recessed to the detonation chamber medial axis.
3. the detonation chamber of pulse-knocking engine according to claim 1 is characterized in that: said contraction section and Drainage Section form the distance of structure of contracted channel less than 0.15 times of detonation chamber internal diameter.
4. the detonation chamber of pulse-knocking engine according to claim 1 is characterized in that: said Drainage Section straight section and motor wall are at a distance of less than 0.15 times of detonation chamber internal diameter.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220132764 CN202578942U (en) | 2012-03-31 | 2012-03-31 | Detonation chamber for pulse detonation engine |
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| Application Number | Priority Date | Filing Date | Title |
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| CN 201220132764 CN202578942U (en) | 2012-03-31 | 2012-03-31 | Detonation chamber for pulse detonation engine |
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| CN202578942U true CN202578942U (en) | 2012-12-05 |
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| CN 201220132764 Withdrawn - After Issue CN202578942U (en) | 2012-03-31 | 2012-03-31 | Detonation chamber for pulse detonation engine |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102606343A (en) * | 2012-03-31 | 2012-07-25 | 西北工业大学 | Detonation chamber of pulse detonation engine |
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- 2012-03-31 CN CN 201220132764 patent/CN202578942U/en not_active Withdrawn - After Issue
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102606343A (en) * | 2012-03-31 | 2012-07-25 | 西北工业大学 | Detonation chamber of pulse detonation engine |
| CN102606343B (en) * | 2012-03-31 | 2013-12-25 | 西北工业大学 | Detonation chamber of pulse detonation engine |
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| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20121205 Effective date of abandoning: 20131225 |
|
| RGAV | Abandon patent right to avoid regrant |