CN104792534B - Rotate detonation engine experimental provision - Google Patents
Rotate detonation engine experimental provision Download PDFInfo
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- CN104792534B CN104792534B CN201510055761.1A CN201510055761A CN104792534B CN 104792534 B CN104792534 B CN 104792534B CN 201510055761 A CN201510055761 A CN 201510055761A CN 104792534 B CN104792534 B CN 104792534B
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Abstract
Detonation engine experimental provision is rotated the present invention relates to one kind, belongs to engine research field.Control ring is inputted including end cap, outer wall, inner chamber and fuel；Screw, oxygen input port are distributed with end cap；Screw, fueling ports are distributed with outer wall, igniter places mouth, and sensor places mouth；Screw is distributed with inner chamber, oxygen is in the entrance of toroidal combustion chamber, entrance of the fuel in toroidal combustion chamber；Through hole is distributed with fuel input control ring；The rotation detonation engine experimental provision of the present invention, oxygen is 1mm in the inlet diameter of toroidal combustion chamber, and quantity reaches 100；Enable to more uniform, the possibility of the continuous rotation detonation phenomena of raising generation in circulating line of fuel and oxygen mix.
Description
Technical field
Detonation engine experimental provision is rotated the present invention relates to one kind, belongs to engine research field.
Background technology
It is a kind of new detonation engine to rotate detonation engine.Because its detonation wave long-term existence is in toroidal combustion chamber
In, and motion state is constantly in, therefore without at a high speed come the igniting flowed and do not stopped, also not producing because detonation is exported and induces
Noise.Detonation wave in toroidal combustion chamber circumferentially continuously propagate by rotation, and high pressure detonation product expands rapidly, along axle
Discharged to high speed, so as to produce propulsive force.Therefore, in terms of propulsion, rotation detonation engine has been provided simultaneously with pulse detonation hair
Motivation and in some advantages for determining detonation engine, i.e.,：Can be with zero starting, the heat that noise is small, detonation product pollution is small, higher
Efficiency, simple in construction, small volume, bigger thrust-weight ratio, working range are wider, can install jet pipe additional produces vectored thrust, and increase flies
Capable mobility.The new type power that ripe rotation detonation engine technology can be used in terms of guided missile and aerospace carrier vehicle
Equipment, is preferable detonation propulsion mode, gathers around and have broad application prospects.
The existing experimental study to rotating detonation engine is less and problem also compares many, such as Peking University Wang Jianping professors
Experimental study to rotating detonation engine【Shock wave is to detonation wave in the such as Li Yang, Wang Zihui, Liu Yusi rotation detonation engines
The national shock wave in Experimental Research [C] // 16th of propagation effect and shock tube academic meeting paper collection .2014:505-
512.】, experimental provision has that sensor places unreasonable, fuel and oxygen mix is of low quality and can not.
The content of the invention
The invention aims to solve present in existing related experiment technology sensor place unreasonable, fuel and
Oxygen mix is of low quality and nonadjustable problem rotates detonation engine experimental provision there is provided one kind.
The purpose of the present invention is achieved through the following technical solutions.
Rotate detonation engine experimental provision, including end cap, outer wall, inner chamber and fuel input control ring；Divide on end cap
It is furnished with screw, oxygen input port；Screw, fueling ports are distributed with outer wall, igniter places mouth, and sensor places mouth；It is interior
Screw is distributed with chamber, oxygen is in the entrance of toroidal combustion chamber, entrance of the fuel in toroidal combustion chamber；In fuel input control ring
Through hole is distributed with；
Annexation：
End cap is that with stepped cylinder, screw, oxygen input port is distributed with end cap；
Outer wall is hollow cylinder, and cylinder Basolateral has is provided with groove on the inside of boss, bottom；It is distributed with outer wall
Screw, fueling ports, igniter places mouth, and sensor places mouth；Sensor places line and the axis of mouth into angle, and
And sensor places the distance between mouth equalization；
Inner chamber is the reeded cylinder in one end, and the projection of groove part and end cap is to agreeing with；There is middle cavity inside
Body, for storing oxygen；Entrance 7 of the oxygen in toroidal combustion chamber, entrance 7 of the oxygen in toroidal combustion chamber are distributed with inner chamber
Inputted in fuel between control ring boss and igniter placement mouth 4；
Fuel input control ring is hollow circular cylinder, and there is boss inner side, and the gap between boss and inner chamber is that fuel exists
The entrance of toroidal combustion chamber；Through hole is offered in fuel input control ring, with the fueling ports on outer wall in same position, is made
Obtain fuel and pass sequentially through the entrance arrival toroidal combustion chamber of fueling ports, through hole and fuel in toroidal combustion chamber；
End cap is connected with inner chamber using bolt；Fuel input control ring is positioned in the groove on the inside of outer wall bottom；
End cap is connected with placed the outer wall of fuel input control ring using bolt.
The course of work：
Oxygen input port is connected with oxygen tank using the pipeline for being mounted with electromagnetic valve；By fueling ports and fuel
Tank is connected using the pipeline for being mounted with electromagnetic valve and back-flow preventer；The igniter that igniter is inserted on outer wall is placed
Mouthful；The sensor that sensor is inserted on outer wall places mouth and is connected to signal collecting device；Oxygen input tube road, fuel is defeated
The electromagnetic valve and igniter entered on pipeline is connected to control system.
Fuel enters experimental facilities by fueling ports, then process fuel enters annular in the entrance of toroidal combustion chamber and fired
Burn room；Oxygen enters experimental facilities by oxygen input port, then eventually enters into annular in the entrance of toroidal combustion chamber by oxygen
Combustion chamber is mixed with fuel.
Input flow rate and the time of oxygen and fuel are controlled using control system, and controls the duration of ignition and energy,
To control the rotation detonation duration, reach Protection device and ensure the purpose of experiment safety.
Rotated using rotating detonation engine experimental provision and can survey out fuel and oxygen in toroidal combustion chamber
The speed along the circumferential direction that the number of detonation wave head during detonation, detonation pressure, detonation wave are propagated and speed in the axial direction,
The data such as the temperature in annular firing room.
Beneficial effect：
1st, rotation detonation engine experimental provision of the invention, the position that pressure sensor places mouth sets more reasonable,
The benefit circumferentially sideling placed be can and meanwhile measure detonation flame circumferentially and central axis direction speed.
2nd, rotation detonation engine experimental provision of the invention, oxygen is 1mm, quantity in the inlet diameter of toroidal combustion chamber
Reach 100；Enable to more uniform, the continuous rotation detonation of raising generation in circulating line of fuel and oxygen mix
The possibility of phenomenon.
3rd, rotation detonation engine experimental provision of the invention, fuel is sized to regulation in the entrance of circulating line, can
To control the input speed and fuel of fuel and the mixing quality of oxygen.
Brief description of the drawings
Fig. 1 is schematic appearance of the invention；
Fig. 2 is left view of the invention；
Fig. 3 is end cap schematic diagram；
Fig. 4 is the A-A profiles of outer wall of the present invention and lumen portion；
Fig. 5 is that fuel inputs control ring and schematic diagram；
Fig. 6 is the diagrammatic cross-section that fuel inputs control ring.
Wherein, 1- screws, 2- oxygen or air-in, 3- fueling ports, 4- igniters place mouth, and 5- sensors are put
Mouth is put, 6- fuel inputs control ring, and 7- oxygen is in the entrance of toroidal combustion chamber, entrance of the 8- fuel in toroidal combustion chamber.
Embodiment
The present invention will be further described with embodiment below in conjunction with the accompanying drawings.
Embodiment 1
Rotate detonation engine experimental provision, including end cap, outer wall, inner chamber and fuel input control ring 6；Divide on end cap
It is furnished with screw 1, oxygen input port 2；Screw 1, fueling ports 3 are distributed with outer wall, igniter places mouth 4, and sensor is placed
Mouth 5；Screw 1 is distributed with inner chamber, oxygen is in the entrance 7 of toroidal combustion chamber, entrance 8 of the fuel in toroidal combustion chamber；Fuel is defeated
Enter and through hole is distributed with control ring；
Annexation：
End cap is that with stepped cylinder, screw 1, oxygen input port 2 is distributed with end cap；
Outer wall is hollow cylinder, and cylinder Basolateral has is provided with groove on the inside of boss, bottom；It is distributed with outer wall
Screw 1, fueling ports 3, igniter places mouth 4, and sensor places mouth 5；Sensor places line and the axis of mouth 5 into folder
Angle, and sensor places the distance between mouth 5 equalization；
Inner chamber is the reeded cylinder in one end, and the projection of groove part and end cap is to agreeing with；There is middle cavity inside
Body, for storing oxygen；Entrance 7 of the oxygen in toroidal combustion chamber, entrance 7 of the oxygen in toroidal combustion chamber are distributed with inner chamber
Inputted in fuel between the boss of control ring 6 and igniter placement mouth 4；
Fuel input control ring 6 is hollow circular cylinder, and there is boss inner side, and the gap between boss and inner chamber is that fuel exists
The entrance 8 of toroidal combustion chamber；Through hole is offered in fuel input control ring 6, with the fueling ports 3 on outer wall in same position
Put so that fuel passes sequentially through fueling ports 3, through hole and fuel and reaches toroidal combustion chamber in the entrance 8 of toroidal combustion chamber；
The external diameter of outer wall afterbody is 210mm, and internal diameter is 150mm, i.e., outer wall afterbody thickness is 30mm；Inner chamber it is a diameter of
140mm, i.e. toroidal combustion chamber thickness are 5mm.
Oxygen input port 2 and a diameter of 10mm of fueling ports 3；Igniter places a diameter of 16mm of mouth 4；Sensing
Device places a diameter of 5mm of mouth 5, and its line and axis are into 45 degree of angles, and sensor places the distance between mouth 5 equalization；
Oxygen is 100 in the quantity of the entrance 7 of toroidal combustion chamber, is uniformly distributed on the circumference of inner chamber, its a diameter of 1mm；Fuel
It is 1mm in the thickness of entrance 8 of toroidal combustion chamber.
End cap is connected with inner chamber using bolt；Fuel input control ring 6 is positioned in the groove on the inside of outer wall bottom；
End cap is connected with placed the outer wall of fuel input control ring 6 using bolt.
The course of work：
Oxygen input port 2 is connected with oxygen tank using the pipeline for being mounted with electromagnetic valve；By fueling ports 3 and combustion
Batch can is connected using the pipeline for being mounted with electromagnetic valve and back-flow preventer；The igniter that igniter is inserted on outer wall is put
Put mouth 4；The sensor that sensor is inserted on outer wall places mouth 5 and is connected to signal collecting device；By oxygen input tube road, combustion
Electromagnetic valve and igniter on material input channel are connected to control system.
Fuel enters experimental facilities by fueling ports 3, then process fuel enters annular in the entrance 8 of toroidal combustion chamber
Combustion chamber；Oxygen enters experimental facilities by oxygen input port 2, then is eventually entered into by oxygen in the entrance 7 of toroidal combustion chamber
Toroidal combustion chamber is mixed with fuel.
Input flow rate and the time of oxygen and fuel are controlled using control system, and controls the duration of ignition and energy,
To control the rotation detonation duration, reach Protection device and ensure the purpose of experiment safety.
Rotated using rotating detonation engine experimental provision and can survey out fuel and oxygen in toroidal combustion chamber
The speed along the circumferential direction that the number of detonation wave head during detonation, detonation pressure, detonation wave are propagated and speed in the axial direction,
The data such as the temperature in annular firing room.
Claims (1)
1. rotate detonation engine experimental provision, it is characterised in that：Control ring is inputted including end cap, outer wall, inner chamber and fuel
(6)；Screw (1), oxygen input port (2) are distributed with end cap；Screw (1), fueling ports (3), igniting are distributed with outer wall
Device places mouth (4), and sensor places mouth (5)；Screw (1) is distributed with inner chamber, oxygen is in the entrance (7) of toroidal combustion chamber, combustion
Expect the entrance (8) in toroidal combustion chamber；Through hole is distributed with fuel input control ring；
End cap is that with stepped cylinder, screw (1), oxygen input port (2) is distributed with end cap；
Outer wall is hollow cylinder, and cylinder Basolateral has is provided with groove on the inside of boss, bottom；Screw is distributed with outer wall
(1), fueling ports (3), igniter places mouth (4), and sensor places mouth (5)；Sensor places the line and axis of mouth (5)
Line is into angle, and sensor places the distance between mouth (5) equalization；
Inner chamber is the reeded cylinder in one end, and the projection of groove part and end cap is to agreeing with；There is hollow cavity inside, uses
In storage oxygen；Entrance (7) of the oxygen in toroidal combustion chamber is distributed with inner chamber, oxygen is in entrance (7) position of toroidal combustion chamber
Inputted in fuel between control ring (6) boss and igniter placement mouth (4)；
Fuel input control ring (6) is hollow circular cylinder, and there is boss inner side, and the gap between boss and inner chamber is fuel in ring
The entrance (8) of shape combustion chamber；Through hole is offered in fuel input control ring (6), with the fueling ports (3) on outer wall same
Position so that fuel passes sequentially through fueling ports (3), through hole and fuel and reaches annular combustion in the entrance (8) of toroidal combustion chamber
Burn room；
End cap is connected with inner chamber using bolt；Fuel input control ring (6) is positioned in the groove on the inside of outer wall bottom；Profit
End cap is connected with placed the outer wall of fuel input control ring (6) with bolt.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201510055761.1A CN104792534B (en) | 2015-02-03 | 2015-02-03 | Rotate detonation engine experimental provision |
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| CN201510055761.1A CN104792534B (en) | 2015-02-03 | 2015-02-03 | Rotate detonation engine experimental provision |
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| CN104792534B true CN104792534B (en) | 2017-10-10 |
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| CN106404337B (en) * | 2016-10-11 | 2019-04-23 | 南京航空航天大学 | Constant volume variable air flow fields corrosion chamber and its working method |
| CN107024355A (en) * | 2017-05-12 | 2017-08-08 | 中国科学院力学研究所 | A kind of method that jet engine high-temperature fuel gas is simulated based on double detonation driven clean gas |
| CN107605600B (en) * | 2017-08-21 | 2019-04-12 | 南京理工大学 | A kind of rotation detonation engine premixing spray |
| US11536456B2 (en) | 2017-10-24 | 2022-12-27 | General Electric Company | Fuel and air injection handling system for a combustor of a rotating detonation engine |
| US11149954B2 (en) | 2017-10-27 | 2021-10-19 | General Electric Company | Multi-can annular rotating detonation combustor |
| CN108256275B (en) * | 2018-03-12 | 2021-02-23 | 北京理工大学 | Numerical simulation ignition detonation method for rotary detonation engine |
| CN109667684B (en) * | 2018-12-26 | 2020-04-14 | 中国人民解放军战略支援部队航天工程大学 | Thrust vector controlled continuous detonation air-breathing engine and aircraft |
| CN109667685B (en) * | 2018-12-26 | 2020-04-10 | 中国人民解放军战略支援部队航天工程大学 | Variable thrust continuous detonation air-breathing engine and aircraft |
| CN109667683B (en) * | 2018-12-26 | 2020-07-17 | 中国人民解放军战略支援部队航天工程大学 | Variable thrust continuous detonation rocket-based engine and aircraft |
| KR20220050909A (en) * | 2019-08-08 | 2022-04-25 | 밴스 터너 | Oxyhydrogen Pulsed and Rotary Detonation Combustion Pumps |
| CN114060854A (en) * | 2021-11-08 | 2022-02-18 | 北京化工大学 | Rotary detonation engine for concentrating detonation waves at inner side of combustion chamber |
| CN114184385A (en) * | 2021-11-15 | 2022-03-15 | 江苏大学 | Double-pulse rotor detonation combustion experimental device and method |
| CN114607526B (en) * | 2022-03-31 | 2024-01-02 | 中国人民解放军战略支援部队航天工程大学 | Impact model engine for researching tangential unstable combustion of double-liquid-phase propellant |
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