CN104895698A - Boosting structure of large-pipe-diameter pulse detonation rocket engine and control method thereof - Google Patents
Boosting structure of large-pipe-diameter pulse detonation rocket engine and control method thereof Download PDFInfo
- Publication number
- CN104895698A CN104895698A CN201510275407.XA CN201510275407A CN104895698A CN 104895698 A CN104895698 A CN 104895698A CN 201510275407 A CN201510275407 A CN 201510275407A CN 104895698 A CN104895698 A CN 104895698A
- Authority
- CN
- China
- Prior art keywords
- detonation
- supply system
- detonation tube
- tube
- fuel oil
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Landscapes
- Fluidized-Bed Combustion And Resonant Combustion (AREA)
Abstract
The invention provides a boosting structure of a large-pipe-diameter pulse detonation rocket engine and a control method thereof. An oxygen supply system, a fuel supply system, an isolation gas supply system and a partitioned detonation tube are involved in the control method. The oxygen supply system comprises a high-pressure gas bottle, a stop valve, a pressure reducing valve, a solenoid valve and a thin hollow tube, wherein small holes are densely distributed in the thin hollow tube in the circumferential direction. The isolation gas supply system comprises a high-pressure gas bottle, a stop valve, a pressure reducing valve, a solenoid valve and four air inlet holes. The fuel supply system comprises an extrusion gas bottle, a pressure reducing valve, an oil bottle, an oil valve and a detonation tube hollow outer wall cavity, wherein fuel oil injection holes are distributed in the detonation tube hollow outer wall cavity. Through control over the pressure reducing valves, the diameter of the small holes in the thin hollow tube and the diameter of the fuel oil injection holes, the supply pressure, equivalence ratio and filling condition of fuel and an oxidizing agent are controlled within an appropriate range, and then continuous and stable detonation waves can be obtained in the partitioned denotation tube. The boosting structure of the large-pipe-diameter pulse detonation rocket engine and the control method thereof have great significance on future development of the pulse detonation engine and can effectively simplify the structure of the engine, improve the filling condition of the engine and improve the average thrust in working of the engine.
Description
Technical field
The present invention relates to pulse-knocking engine technical field, is a kind of push structure and controlling method thereof of Large Diameter Pipeline pulse detonation rocket engines.
Background technique
Pulse detonation rocket engines (Pulse Detonation Rocket Engine is called for short PDRE) is a kind of new concept engine utilizing intermittent type detonation wave to produce thrust.PDRE is as a kind of novel power plant, and because its structure is simple, cycle efficiency is high, and the potential advantage such as the wide and thrust weight ratio of operating range is high, has good application prospect.In recent years, the performance both at home and abroad for improving pulse-knocking engine has done many research work, and makes great progress.
Compared with existing propulsion system, PDRE seems to have very large potential advantages, but these potential advantages will be come true, still face many difficult problems and challenge, one of them crucial problem is exactly how its thrust is increased to the degree that can drop into application to engineering practice.The factor affecting PDRE thrust is a lot, and this wherein, and the size of PDRE detonation tube caliber is the principal element determining its thrust size, but when the caliber of detonation tube increases to a certain degree, detonation wave will be difficult to proper detonation and control oneself.In order to address this problem, that most of research team all adopts in the world at present is multibarrel PDRE, is realized the increase of thrust by the quantity increasing detonation tube.This method is no doubt feasible, but multibarrel PDRE can take a large amount of volumes, and it is many that the deadweight of PDRE can be made to increase, and this causes very large burden by PDRE.
At present, what the fuel of most PDRE and oxygenant supply mode all adopted is head supply, and such supply mode makes the overall structure of PDRE more short and sweet, but this supply mode also exists great defect also.When the frequency of okperation of PDRE is very high, within the filling time of one-period, oxygenant and fuel can not be filled up rapidly whole detonation tube by simple head supply, and this will cause the degree of filling of detonation tube too low, thus affects the stable operation of pinking effect and PDRE.In order to address this problem, some research institutions propose the distributed supply of fuel and oxygenant, make the filling of whole detonation tube more abundant.
Summary of the invention
The technical problem solved
Improve the frequency of okperation of pulse-knocking engine and expand two kinds of major ways that detonation tube caliber is its average thrust of raising.Be difficult to proper detonation to solve detonation wave in Large Diameter Pipeline situation and control oneself, and detonation tube degree of filling this two problems too low in high-frequency work situation, the present invention proposes the detonation tube using partition type, and adopt the distributed supply mode of fuel and oxygenant.Use detonation tube designed in the present invention, and according to correct operating procedure, successfully can realize the high-frequency work of Large Diameter Pipeline pulse-knocking engine.
Technological scheme of the present invention is:
A kind of push structure of Large Diameter Pipeline pulse detonation rocket engines and controlling method thereof, comprise fuel supply system, oxygen supply system, separation gas supply system, and partition type detonation tube device, it is characterized in that: the detonation tube of a Large Diameter Pipeline is divided into four identical being in charge of of size, a hollow pipeline is passed into as oxygen supply system at the circle centre position of detonation tube, make a call to the supply system of a hole as separation gas each point of tube hub of the head of detonation tube is each, the supply system of fuel oil as fuel is passed in the hollow outer wall chamber of detonation tube, and in detonation tube each is in charge of, respectively fill a waypoint firearm.
The push structure of described a kind of Large Diameter Pipeline pulse detonation rocket engines and controlling method thereof, it is characterized in that: the Large Diameter Pipeline detonation tube being difficult to detonate by is divided into the identical fan-shaped detonation tube of four sizes, solve the problem that the excessive detonation wave caused of detonation tube caliber is difficult to detonate and control oneself.
The push structure of described a kind of Large Diameter Pipeline pulse detonation rocket engines and controlling method thereof, it is characterized in that: use a circumference to be covered with the hollow tubule of aperture, and at its head, a solenoid valve is installed, as the supply system of oxygen, traditional axial direct-lighting type air feed is improved to the distributed air feed along tubule circumference, this feature will make the filling of oxygen more all fully even, and this structure being similar to porous cooling also can have certain cooling action to tube wall simultaneously.
The push structure of described a kind of Large Diameter Pipeline pulse detonation rocket engines and controlling method thereof, it is characterized in that: make a call to a hole the head wall center of the independent detonation tube of each separation is each, and at detonation tube head, a solenoid valve is installed, the waste gas burnt blows down by separation gas axial admission.
The push structure of described a kind of Large Diameter Pipeline pulse detonation rocket engines and controlling method thereof, it is characterized in that: in the outer wall cavity of detonation tube, pass into fuel oil, on the internal face of each independent detonation tube outer wall, make a call to row's oil burning jet orifice vertically with the span of 100mm, the direction in hole is inwardly perpendicular to axial direction.At detonation tube oil pocket, a fuel tap is installed outward, controls the filling of fuel oil, form the fuel oil supply system of whole detonation tube thus.First this system achieves the distributed supply of fuel oil, makes the filling of fuel oil more all fully even; Secondly, the fuel oil passed into can cool the detonation tube wall of high temperature, and the fuel oil after preheating also more easily detonates after spraying into detonation tube, thus realizes the re-generatively cooled of fuel oil; Again, the fuel oil sprayed into can form fluid barrier, the formation of acceleration knock ripple, and shortens the distance of DDT (Deflagration to Detonation Transition) section.
Beneficial effect
Adopt efficient push structure and the controlling method thereof of Large Diameter Pipeline pulse detonation rocket engines provided by the invention, the detonation tube of a Large Diameter Pipeline is divided into the detonation tube that four sizes are identical, the problem that Large Diameter Pipeline detonation tube is difficult to detonate can be solved, and, compared to multibarrel pulse-knocking engine, this method reduces the volume and weight of pulse-knocking engine greatly.The fuel that the present invention adopts and the distributed supply mode of oxygenant, structure is simple, save space, and under successfully can solving PDRE high-frequency work state, independent head supplies the problem of the degree of filling deficiency caused.Meanwhile, fuel delivery mode of the present invention successfully achieves the re-generatively cooled of fuel oil, and defines fluid barrier, accelerates the formation of detonation wave.
Accompanying drawing explanation
Fig. 1: system schematic of the present invention
Fig. 2: the head schematic cross-section of detonation tube
Fig. 3: in an operation cycle, the Control timing sequence figure of solenoid valve and igniter
Wherein, 1-1 is oxygenant gas cylinder, and 1-2 is oxygenant stop valve, and 1-3 is oxygenant reduction valve, and 1-4 is oxidant inlet solenoid valve, and 1-5 is the oxygenant supply hollow pipe that circumference is covered with aperture; 2-1 is separation gas gas cylinder, and 2-2 is separation gas stop valve, and 2-3 is separation gas reduction valve, and 2-4 is separation gas import solenoid valve, and 2-51,2-52,2-53,2-54 are four imports of separation gas at detonation tube head; 3-1,3-2,3-3,3-4 are four igniters of detonation tube circumference; 4-1 is liquid fuel bottle, and 4-2 is liquid fuel stop valve, and 4-3 is liquid fuel inlet solenoid valve, and 4-4 is the hollow outer wall chamber of detonation tube passing into liquid fuel, and 4-5 is fuel injection aperture perpendicular to axial direction; 5-1 is fuel oil extruding gas cylinders, and 5-2 is fuel oil extruding gas pressure reducer; 6-1,6-2,6-3,6-4 are dividing plate Large Diameter Pipeline detonation tube being divided into the quartering.
Embodiment
Below in conjunction with instantiation and accompanying drawing, the invention will be further described
The control gear of the partition type pulse-knocking engine in the present embodiment comprises separation gas supply system, oxygen supply system and fuel supply system.
Separation gas supply system is made up of four separation gas import 2-5 of separation gas gas cylinder 2-1, separation gas stop valve 2-2, separation gas reduction valve 2-3, separation gas import solenoid valve 2-4 and detonation tube head.
The oxygenant supply hollow pipe 1-5 that oxygen supply system is covered with aperture by oxygenant gas cylinder 1-1, oxygenant stop valve 1-2, oxygenant reduction valve 1-3, oxidant inlet solenoid valve 1-4 and circumference forms.
Fuel supply system is by extruding gas cylinders 5-1, extruding gas pressure reducer 5-2, liquid fuel bottle 4-1, liquid fuel stop valve 4-2, liquid fuel inlet solenoid valve 4-3, the detonation tube hollow outer wall chamber 4-4 passing into liquid fuel, fuel injection aperture 4-5 perpendicular to axial direction.
In the present embodiment, the fuel of employing is aviation kerosine, and oxygenant is oxygen, and separation gas is nitrogen, and fuel oil extruding gas is nitrogen, and what igniter adopted is automobile spark plug.The diameter of the fuel injection aperture on the hollow outer wall chamber of detonation tube is 0.2 ~ 0.5mm, and the hole diameter be responsible on the hollow pipe of oxygenant supply is 0.5 ~ 2mm, and the separation gas inlet diameter of detonation tube head is 10mm.At the equidistant installation of the pinking propagation segment of the detonation tube of each separation 4 pressure transducers, measure the pressure everywhere of detonation tube respectively.
In the present embodiment, oxygenant after reduction valve and separation gas pressure are respectively 1.5MPa and 0.6MPa, fuel oil extruding gas pressure after reduction valve is 0.5MPa, external pressure and temperature are respectively 0.101325MPa and 288K, in this case, the equivalent proportion of aviation kerosine and oxygen is approximately 1.0.In such a situa-tion, commonly use software for calculation CEA (Chemical Equilibrium and Applications) by pinking and can calculate the pressure of detonation wave and speed is respectively 4.078MPa and 2302m/s.
During work, need between each path to supply according to certain Control timing sequence.Solenoid valve as shown in Figure 3 and igniter Control timing sequence figure, in a control cycle, the solenoid valve of oxygenant supply system and the fuel tap working state of fuel oil supply system completely the same.In the incipient stage of each control cycle, solenoid valve 1-4 and 4-3 of oxygenant and fuel oil opens simultaneously, the detonation tube that four are separated is filled, for igniting is subsequently ready, oxygenant and fuel solenoid valve 1-4 and 4-3 close simultaneously afterwards, use igniter 3-1,3-2,3-3,3-4 to light a fire to four detonation tubes, the fuel oil in detonation tube is lighted simultaneously, finally forms detonation wave through the continuous differentiation in whole detonation tube and propagates out outside pipe.Subsequently, open the solenoid valve 2-4 of separation gas supply system, waste gas in detonation tube is blown down, until close separation gas solenoid valve 2-4 at the end of a control cycle by four separation gas imports 2-51,2-52,2-53,2-54 of detonation tube head.For the frequency of okperation of 30Hz, the operating phase of oxygenant and fuel oil supply system solenoid valve is 0 °, and dutycycle is 0.4; The operating phase of separation gas supply system solenoid valve is 251 °, and dutycycle is 0.3; The operating phase of fire signal is 144 °, and dutycycle is 0.03.
In the present embodiment, utilize solenoid valve to carry out the work schedule of controlled oxidization agent, fuel and separation gas, successfully can realize the continous-stable work of partition type pulse-knocking engine.Meanwhile, utilize the time dependent curve of pressure being arranged on the pressure transducer on detonation tube and collecting, can judge whether to define detonation wave.Thus, adopt method provided by the invention, just can produce the detonation wave of continous-stable in Large Diameter Pipeline pulse detonation rocket engines.
Claims (5)
1. the push structure of a Large Diameter Pipeline pulse detonation rocket engines and controlling method thereof, comprise fuel supply system, oxygen supply system, separation gas supply system, and partition type detonation tube device, it is characterized in that: the detonation tube of a Large Diameter Pipeline is divided into four identical being in charge of of size, a hollow pipeline is passed into as oxygen supply system at the circle centre position of detonation tube, make a call to the supply system of a hole as separation gas each point of tube hub of the head of detonation tube is each, the supply system of fuel oil as fuel is passed in the hollow outer wall chamber of detonation tube, and in detonation tube each is in charge of, respectively fill a waypoint firearm.
2. the push structure of a kind of Large Diameter Pipeline pulse detonation rocket engines according to claims 1 and controlling method thereof, is characterized in that: the Large Diameter Pipeline detonation tube being difficult to detonate by is divided into the identical fan-shaped detonation tube of four sizes.
3. the efficient push structure of a kind of Large Diameter Pipeline pulse detonation rocket engines according to claims 1 and controlling method thereof, it is characterized in that: use a circumference to be covered with the hollow tubule of aperture, and at its head, a solenoid valve is installed, as the supply system of oxygen, traditional axial direct-lighting type air feed is improved to the distributed air feed along tubule circumference.
4. the push structure of a kind of Large Diameter Pipeline pulse detonation rocket engines according to claims 1 and controlling method thereof, it is characterized in that: make a call to a hole the head wall center of the independent detonation tube of each separation is each, and at detonation tube head, a solenoid valve is installed, the waste gas burnt blows down by separation gas axial admission.
5. the push structure of a kind of Large Diameter Pipeline pulse detonation rocket engines according to claims 1 and controlling method thereof, it is characterized in that: in the outer wall cavity of detonation tube, pass into fuel oil, on the internal face of each independent detonation tube outer wall, make a call to row's oil burning jet orifice vertically with the span of 100mm, the direction in hole is inwardly perpendicular to axial direction.At detonation tube oil pocket, a fuel tap is installed outward, controls the filling of fuel oil, form the fuel oil supply system of whole detonation tube thus.First this system achieves the distributed supply of fuel oil, makes the filling of fuel oil more all fully even; Secondly, the fuel oil passed into can cool the detonation tube wall of high temperature, and the fuel oil after preheating also more easily detonates after spraying into detonation tube, thus realizes the re-generatively cooled of fuel oil; Again, the fuel oil sprayed into can form fluid barrier, the formation of acceleration knock ripple, and the distance shortening DDT section.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510275407.XA CN104895698A (en) | 2015-05-19 | 2015-05-19 | Boosting structure of large-pipe-diameter pulse detonation rocket engine and control method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510275407.XA CN104895698A (en) | 2015-05-19 | 2015-05-19 | Boosting structure of large-pipe-diameter pulse detonation rocket engine and control method thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104895698A true CN104895698A (en) | 2015-09-09 |
Family
ID=54028593
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510275407.XA Pending CN104895698A (en) | 2015-05-19 | 2015-05-19 | Boosting structure of large-pipe-diameter pulse detonation rocket engine and control method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104895698A (en) |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107044361A (en) * | 2017-05-17 | 2017-08-15 | 西北工业大学 | A kind of pulse detonation rocket engines and control method with combustion-compensating device |
| CN109184950A (en) * | 2018-09-25 | 2019-01-11 | 西北工业大学 | A kind of device of low energy igniting starting detonation wave |
| CN109209678A (en) * | 2018-09-18 | 2019-01-15 | 西北工业大学 | A kind of pulse-knocking propulsion device based on re-generatively cooled structure |
| CN109209681A (en) * | 2018-10-08 | 2019-01-15 | 西北工业大学 | A kind of pulse-knocking engine detonation tube structure of reverse-flow type |
| CN109404165A (en) * | 2018-12-26 | 2019-03-01 | 中国人民解放军战略支援部队航天工程大学 | The continuous pinking rocket base engine and aircraft of thruster vector control |
| CN109915281A (en) * | 2019-03-06 | 2019-06-21 | 西北工业大学 | A kind of pulse detonation rocket engines fuel feeding scheme being beneficial to wall cooling and detonation |
| CN111535939A (en) * | 2019-12-12 | 2020-08-14 | 西北工业大学 | Fuel injection system and method suitable for regenerative cooling detonation combustion chamber |
| CN113088861A (en) * | 2021-04-07 | 2021-07-09 | 西北工业大学 | Small-size explosion spraying device of efficient |
| CN114060852A (en) * | 2021-11-18 | 2022-02-18 | 河南理工大学 | Double-cavity type premixing flame accelerating device |
| CN117341994A (en) * | 2023-10-18 | 2024-01-05 | 东方空间技术(山东)有限公司 | Cold air pushing system and cold air pushing method |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101012786A (en) * | 2006-09-20 | 2007-08-08 | 西北工业大学 | High-frequency pulse pinking engine and control method thereof |
| CN101749143A (en) * | 2009-12-14 | 2010-06-23 | 西北工业大学 | Distribution-type spouting mechanism of secondary propellant of pulse detonation engine |
| CN101776026A (en) * | 2010-02-04 | 2010-07-14 | 西北工业大学 | Air inlet of air-breathing pulse detonation engine |
| EP2327867A2 (en) * | 2009-11-30 | 2011-06-01 | General Electric Company | Thrust modulation in a multiple combustor pulse detonation engine using cross-combustor detonation initiation |
| CN201858046U (en) * | 2010-11-11 | 2011-06-08 | 西北工业大学 | Pulse detonation engine realizing secondary detonation |
| CN103075271A (en) * | 2013-01-21 | 2013-05-01 | 西北工业大学 | High-frequency conical spiral tube type pulse detonation engine |
| CN103195613A (en) * | 2013-04-15 | 2013-07-10 | 西北工业大学 | Pulse detonation rocket engine frequency doubling work control device and control method thereof |
| CN103291499A (en) * | 2013-06-08 | 2013-09-11 | 西北工业大学 | Method for achieving pulse detonation rocket engine high-frequency work |
-
2015
- 2015-05-19 CN CN201510275407.XA patent/CN104895698A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101012786A (en) * | 2006-09-20 | 2007-08-08 | 西北工业大学 | High-frequency pulse pinking engine and control method thereof |
| EP2327867A2 (en) * | 2009-11-30 | 2011-06-01 | General Electric Company | Thrust modulation in a multiple combustor pulse detonation engine using cross-combustor detonation initiation |
| CN101749143A (en) * | 2009-12-14 | 2010-06-23 | 西北工业大学 | Distribution-type spouting mechanism of secondary propellant of pulse detonation engine |
| CN101776026A (en) * | 2010-02-04 | 2010-07-14 | 西北工业大学 | Air inlet of air-breathing pulse detonation engine |
| CN201858046U (en) * | 2010-11-11 | 2011-06-08 | 西北工业大学 | Pulse detonation engine realizing secondary detonation |
| CN103075271A (en) * | 2013-01-21 | 2013-05-01 | 西北工业大学 | High-frequency conical spiral tube type pulse detonation engine |
| CN103195613A (en) * | 2013-04-15 | 2013-07-10 | 西北工业大学 | Pulse detonation rocket engine frequency doubling work control device and control method thereof |
| CN103291499A (en) * | 2013-06-08 | 2013-09-11 | 西北工业大学 | Method for achieving pulse detonation rocket engine high-frequency work |
Non-Patent Citations (2)
| Title |
|---|
| 宫继双等: ""扇环形截面管内爆震波特性研究"", 《工程热物理学报》 * |
| 胡承启: ""脉冲爆震火箭发动机性能的实验研究"", 《中国优秀博硕士学位论文全文数据库 工程科技Ⅱ辑》 * |
Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107044361A (en) * | 2017-05-17 | 2017-08-15 | 西北工业大学 | A kind of pulse detonation rocket engines and control method with combustion-compensating device |
| CN109209678A (en) * | 2018-09-18 | 2019-01-15 | 西北工业大学 | A kind of pulse-knocking propulsion device based on re-generatively cooled structure |
| CN109209678B (en) * | 2018-09-18 | 2020-12-08 | 西北工业大学 | Pulse detonation propulsion device based on regenerative cooling structure |
| CN109184950B (en) * | 2018-09-25 | 2020-09-01 | 西北工业大学 | Device of low energy ignition initiating detonation wave |
| CN109184950A (en) * | 2018-09-25 | 2019-01-11 | 西北工业大学 | A kind of device of low energy igniting starting detonation wave |
| CN109209681A (en) * | 2018-10-08 | 2019-01-15 | 西北工业大学 | A kind of pulse-knocking engine detonation tube structure of reverse-flow type |
| CN109404165A (en) * | 2018-12-26 | 2019-03-01 | 中国人民解放军战略支援部队航天工程大学 | The continuous pinking rocket base engine and aircraft of thruster vector control |
| CN109915281B (en) * | 2019-03-06 | 2021-03-19 | 西北工业大学 | Pulse detonation rocket engine oil supply scheme beneficial to wall cooling and detonation |
| CN109915281A (en) * | 2019-03-06 | 2019-06-21 | 西北工业大学 | A kind of pulse detonation rocket engines fuel feeding scheme being beneficial to wall cooling and detonation |
| CN111535939A (en) * | 2019-12-12 | 2020-08-14 | 西北工业大学 | Fuel injection system and method suitable for regenerative cooling detonation combustion chamber |
| CN111535939B (en) * | 2019-12-12 | 2022-05-27 | 西北工业大学 | Fuel injection system suitable for regenerative cooling detonation combustion chamber |
| CN113088861A (en) * | 2021-04-07 | 2021-07-09 | 西北工业大学 | Small-size explosion spraying device of efficient |
| CN114060852A (en) * | 2021-11-18 | 2022-02-18 | 河南理工大学 | Double-cavity type premixing flame accelerating device |
| CN117341994A (en) * | 2023-10-18 | 2024-01-05 | 东方空间技术(山东)有限公司 | Cold air pushing system and cold air pushing method |
| CN117341994B (en) * | 2023-10-18 | 2024-03-22 | 东方空间技术(山东)有限公司 | Cold air pushing system and cold air pushing method |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104895698A (en) | Boosting structure of large-pipe-diameter pulse detonation rocket engine and control method thereof | |
| CN103899435B (en) | A kind of combined type pulse detonation engine detonation chamber | |
| CN101881238A (en) | Air-breathing pulse detonation engine and detonation method thereof | |
| CN104154567B (en) | A kind of rotation detonation combustor | |
| CN204042975U (en) | A kind of rotation detonation combustor | |
| CN102003303B (en) | Pulse detonation engine with secondary detonation | |
| CN104792534A (en) | Rotation detonation engine experimental device | |
| CN107605603B (en) | A kind of ignition system for pulse-knocking engine | |
| CN104265506B (en) | Pulse-knocking engine | |
| CN204082338U (en) | A kind of rotation pinking gas turbine | |
| CN201858046U (en) | Pulse detonation engine realizing secondary detonation | |
| CN103075270A (en) | High-pressure-intensity external pulse excitation device for T-shaped burner | |
| CN104500272A (en) | Low-flow-resistant near-wall small-space annular shock wave focusing direct priming device | |
| CN103899436B (en) | A kind of spiral multichannel pulse-knocking engine | |
| CN107044361A (en) | A kind of pulse detonation rocket engines and control method with combustion-compensating device | |
| CN101839166B (en) | Lateral-swirl combustion chamber | |
| CN101985904B (en) | Control method of detonation pipe for high-frequency pulse detonation engine | |
| CN104033286A (en) | High-frequency impulse knocking combustion power plant | |
| CN114183773A (en) | Combustion chamber capable of generating multiple rotary detonation waves | |
| CN102606343B (en) | Detonation chamber of pulse detonation engine | |
| CN109681678B (en) | Pneumatic valve for pulse detonation engine | |
| CN203962199U (en) | A kind of high-frequency pulse pinking combustion-powered apparatus | |
| CN206338123U (en) | A kind of rotary engine of independent compression stroke | |
| CN202005180U (en) | Body-spread catalyst spreading device for hail suppression and rain enhancement | |
| CN109458274A (en) | A kind of variable cross-section petaloid mixer-ejector suitable for pulse-knocking engine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20150909 |