CN113756990B - Bypass air-entraining low-energy ignition return type detonating device - Google Patents
Bypass air-entraining low-energy ignition return type detonating device Download PDFInfo
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- CN113756990B CN113756990B CN202110715235.9A CN202110715235A CN113756990B CN 113756990 B CN113756990 B CN 113756990B CN 202110715235 A CN202110715235 A CN 202110715235A CN 113756990 B CN113756990 B CN 113756990B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/95—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by starting or ignition means or arrangements
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02P—IGNITION, OTHER THAN COMPRESSION IGNITION, FOR INTERNAL-COMBUSTION ENGINES; TESTING OF IGNITION TIMING IN COMPRESSION-IGNITION ENGINES
- F02P5/00—Advancing or retarding ignition; Control therefor
- F02P5/04—Advancing or retarding ignition; Control therefor automatically, as a function of the working conditions of the engine or vehicle or of the atmospheric conditions
- F02P5/145—Advancing or retarding ignition; Control therefor automatically, as a function of the working conditions of the engine or vehicle or of the atmospheric conditions using electrical means
- F02P5/15—Digital data processing
- F02P5/152—Digital data processing dependent on pinking
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- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Signal Processing (AREA)
- Ignition Installations For Internal Combustion Engines (AREA)
- Combustion Methods Of Internal-Combustion Engines (AREA)
Abstract
The utility model relates to a bypass bleed low energy ignition passback formula priming device, its technical field who is applied to rotatory detonation engine, it includes by-pass pipe, ignition unit and the control unit, be equipped with on the annular combustion chamber be used for with the opening of by-pass pipe intercommunication, by-pass pipe one end and annular combustion chamber intercommunication, the laminating of by-pass pipe lateral wall sets up on the outer wall of annular combustion chamber, the ignition unit with the control unit all install in on the by-pass pipe, the control unit is located the ignition unit is kept away from open-ended one side is used for control by-pass pipe opens and shuts. The rotary detonation engine has the advantages of being simple in structure, small in occupied space, capable of effectively reducing the volume of the rotary detonation engine, saving manufacturing cost and achieving the effect of overcoming the restarting problem of the rotary detonation engine.
Description
Technical Field
The application relates to the technical field of rotary detonation engines, in particular to a bypass air-entraining low-energy ignition return type detonating device.
Background
With the rapid development of aerospace industry, a propulsion system which is higher in efficiency, speed, thrust-weight ratio and reliability than a traditional turbine engine is needed, and therefore researchers provide a rotary detonation engine. The rotary detonation engine ignites premixed gas in the annular combustion chamber through single ignition and forms detonation waves, fuel is continuously injected into the annular combustion chamber from the closed end at a high speed, the detonation waves can continuously rotate along the circumferential direction, and combustion products are ejected from the other open end through axial expansion, so that thrust is generated.
In the related art, for the priming device of the rotary knocking engine, the following three methods are generally used: a pre-squib igniter, a hot jet igniter, and a charge igniter.
The pre-explosion tube igniter is provided with a pre-explosion tube communicated with a combustion chamber of an engine, fuel is sprayed into the pre-explosion tube, the fuel in the pre-explosion tube is ignited, the fuel in the pre-explosion tube is instantaneously combusted to generate deflagration, detonation waves are developed in the pre-explosion tube, and the detonation waves are transmitted into the annular combustion chamber to achieve the effect of detonating the fuel in the annular combustion chamber; a length of passage is required in the pre-squib due to the need to generate the detonation wave.
The hot jet igniter sprays fuel into the precombustion chamber to ignite the precombustion chamber through arranging the precombustion chamber communicated with the combustion chamber of the engine, and the generated flame beams are quickly sprayed into the annular combustion chamber to achieve the effect of igniting the fuel in the annular combustion chamber.
The explosive column igniter is provided with an explosive column, and the fuel in the annular combustion chamber is detonated by detonating the explosive column.
Aiming at the related technologies, a pre-explosion tube igniter and a hot jet igniter both need to be provided with a new structure on the side wall of the rotary detonation engine, and meanwhile, an independent oil and gas supply circuit needs to be arranged for the pre-explosion tube and the pre-combustion chamber in a matched manner, particularly, the pre-explosion tube igniter needs to be provided with a pre-explosion tube with a certain length, while an explosive column igniter can only ignite once, a spacecraft cannot ignite twice in the air, and the ignition cost is high, and the inventor thinks that the defects of complex structure, large occupied space and high manufacturing cost of a rotary detonation engine detonating device exist.
Disclosure of Invention
In order to solve the problems of complex structure, large occupied space and high manufacturing cost, the application provides a bypass air-entraining low-energy ignition return type detonating device.
The application provides a bypass bleed air low energy ignition passback formula priming device adopts following technical scheme:
the bypass air entraining low-energy ignition return type detonating device comprises a branch pipe, an ignition unit and a control unit, wherein an opening used for being communicated with the branch pipe is formed in an annular combustion chamber, one end of the branch pipe is communicated with the annular combustion chamber, the side wall of the branch pipe is attached to the outer wall of the annular combustion chamber, the ignition unit and the control unit are both mounted on the branch pipe, and the control unit is located on one side, far away from the opening, of the ignition unit and used for controlling the branch pipe to open and close.
By adopting the technical scheme, the branch pipe is communicated with the annular combustion chamber, after the rotary detonation engine is started, the fuel sprayed into the annular combustion chamber can enter the branch pipe, the control unit closes the branch pipe, the ignition unit is started to ignite the fuel in the branch pipe, the fuel in the branch pipe is instantaneously combusted to generate deflagration, and the detonation wave is developed in the branch pipe, the detonation wave is transmitted into the annular combustion chamber to detonate the fuel in the annular combustion chamber, after the rotary detonation engine is closed, the branch pipe is opened through the control unit to discharge waste gas, because the actions can be repeated, the problem of restarting the rotary detonation engine is solved, because the branch pipe is attached to the outer wall of the annular combustion chamber and shares one path of fuel with the annular combustion chamber, therefore, the structure is simplified, the occupied space is small, the size of the rotary detonation engine can be effectively reduced, and the manufacturing cost is saved.
Preferably, the branch pipe is wound along the circumferential direction of the outer wall of the annular combustion chamber.
By adopting the technical scheme, the branch pipe is wound along the circumferential direction of the outer wall of the annular combustion chamber, so that the size of the rotary detonation engine is saved, and the length required by the branch pipe can be met.
Preferably, the bypass duct is arranged to meander along the outer wall of the annular combustion chamber.
By adopting the technical scheme, when the outer wall of the annular combustion chamber is partially connected with other parts, the branch pipe is arranged along the outer wall of the annular combustion chamber in a winding manner, so that the volume of the rotary detonation engine is saved, and the length required by the branch pipe can be met.
Preferably, the control unit includes a solenoid valve, and the solenoid valve is installed on the branch pipe.
By adopting the technical scheme, the electromagnetic valve is arranged, and the opening and closing of the branch pipe can be conveniently controlled.
Preferably, the control unit further comprises a time schedule controller, and the time schedule controller (32) is connected with the electromagnetic valve.
By adopting the technical scheme, after the rotary detonation engine is started, the electromagnetic valve is set by the time schedule controller to delay for closing for a certain time, so that fuel in the annular combustion chamber can be ensured to enter the branch pipe, waste gas or air in the branch pipe is extruded, the branch pipe is filled with the fuel, and the probability of successful ignition of the ignition unit is improved.
Preferably, the ignition unit is a spark plug.
By adopting the technical scheme, the ignition effect is stable, the structure is small, the price is low, and the installation is convenient.
Preferably, be provided with torsional spring and valve on the bypath pipe, a plurality of through-holes have been seted up to the valve, the valve install in the opening part is articulated with annular combustion chamber, just the articulated shaft of valve sets up along the axial of annular combustion chamber, the torsional spring cover is located on the articulated shaft.
Through adopting above-mentioned technical scheme, seted up a plurality of through-holes on the valve, do not influence fuel and get into the branch road pipe, after the branch road pipe is igniteed, produce the detonation wave and push the valve open and spread into annular combustion chamber for most detonation wave has realized one-way detonation to a certain extent along annular combustion chamber one side transmission, has ignited the back because the effect valve of torsional spring retracts to initial position.
Preferably, the side wall of the opening is provided with a containing groove, and the valve is arranged in the containing groove.
Through adopting above-mentioned technical scheme, the valve sets up in the holding tank, does not have the part that extrudes in the annular combustion chamber, does not influence the burning condition in the annular combustion chamber.
In summary, the present application includes at least one of the following beneficial technical effects:
1. the branch pipe is attached to the outer wall of the annular combustion chamber and shares one path of fuel with the annular combustion chamber, so that the structure is simplified, the occupied space is small, the volume of the rotary detonation engine can be effectively reduced, and the manufacturing cost is saved;
2. the branch pipe is communicated with the annular combustion chamber, fuel sprayed into the annular combustion chamber can enter the branch pipe, and the fuel in the branch pipe can be ignited through the ignition unit and the control unit, so that the problem of restarting the rotary detonation engine is solved;
3. the timing controller is arranged, and the electromagnetic valve is arranged through the timing controller to delay and close for a certain time, so that after the rotary detonation engine is started, fuel in the annular combustion chamber can be ensured to enter the branch pipe, waste gas or air in the branch pipe is extruded out, the branch pipe is filled with the fuel, and the probability of successful ignition of the ignition unit is improved;
4. set up and seted up a plurality of through-holes on valve and the valve, do not influence fuel and get into the branch road pipe, after the branch road pipe ignition, produce the detonation wave and push the valve open and spread into annular combustion chamber for most detonation wave has realized one-way detonation to a certain extent along annular combustion chamber one side transmission, has lighted the back because the effect valve of torsional spring retracts to initial position.
Drawings
Fig. 1 is an overall schematic diagram of a bypass bleed low energy ignition pass-back type detonating device according to embodiment 1 of the present application.
Fig. 2 is a schematic view of a disassembled valve structure in embodiment 1 of the present application.
Fig. 3 is an enlarged schematic view of a portion a of fig. 2.
Fig. 4 is an overall schematic diagram of a bypass bleed low energy ignition pass-back type detonating device of embodiment 2 of the present application.
Fig. 5 is an overall schematic diagram of a bypass bleed low energy ignition pass-back type primer detonator according to embodiment 3 of the present application.
Description of reference numerals: 1. a branch pipe; 11. a valve; 111. a through hole; 112. hinging a shaft; 12. a torsion spring; 2. an ignition unit; 3. a control unit; 31. an electromagnetic valve; 32. a time schedule controller; 4. an annular combustion chamber; 41. an opening; 42. and (6) accommodating the tank.
Detailed Description
The present application is described in further detail below with reference to figures 1-5.
Example 1
The embodiment of the application discloses a bypass air-entraining low-energy ignition return type detonating device. Referring to fig. 1, fig. 2 and fig. 3, a bypass bleed low energy ignition passback formula priming device, including branch pipe 1, ignition unit 2 and the control unit 3, set up opening 41 with branch pipe 1 intercommunication on the annular combustion chamber 4, and opening 41 is located the one end that annular combustion chamber 4 deviates from row waste gas, branch pipe 1 one end weld in opening 41 department and with the intercommunication of annular combustion chamber 4, ignition unit 2 and the control unit 3 are all installed on branch pipe 1, the control unit 3 is located one side that ignition unit 2 kept away from opening 41, be used for controlling opening and shutting of branch pipe 1.
Referring to fig. 1, the port of the bypass pipe 1 of the present embodiment 1 is semicircular, and may be rectangular, circular, or rhombic. The branch pipe 1 is around establishing along the circumferential direction of 4 outer walls of annular combustion chamber, and the laminating of 1 lateral wall of branch pipe welds on 4 outer walls of annular combustion chamber.
Referring to fig. 1 and 2, the ignition unit 2 is a spark plug, and the ignition unit 2 is installed near an end of the bypass pipe 1 away from the opening 41; the control unit 3 comprises an electromagnetic valve 31 and a time schedule controller 32, the electromagnetic valve 31 is installed on the branch pipe 1 and is located on one side, far away from the opening 41, of the ignition unit 2, the electromagnetic valve 31 can close and open the branch pipe 1, the time schedule controller 32 is installed on the electromagnetic valve 31 and is connected with the electromagnetic valve 31, the time schedule controller 32 controls the electromagnetic valve 31 to be closed after delay, after the rotary detonation engine is started, a feeding device sprays fuel into the annular combustion chamber 4, the time schedule controller 32 can enable the electromagnetic valve 31 not to be closed immediately, the fuel in the annular combustion chamber 4 can be guaranteed to enter the branch pipe 1, waste gas or air in the branch pipe 1 is squeezed out, the branch pipe 1 is filled with the fuel, and then the electromagnetic valve 31 is closed to carry out ignition.
Referring to fig. 2 and 3, the bypass pipe 1 is provided with a torsion spring 12 and a valve 11, the valve 11 is provided with a plurality of through holes 111, the inner wall of the opening 41 of the annular combustion chamber 4 is provided with an accommodating groove 42, the valve 11 is arranged in the accommodating groove 42 and hinged to the annular combustion chamber 4, a hinge shaft 112 of the valve 11 is arranged along the axial direction of the annular combustion chamber 4, and the torsion spring 12 is sleeved on the hinge shaft 112.
The implementation principle of the embodiment 1 of the application is as follows:
1. when the rotary detonation engine does not require ignition: the electromagnetic valve 31 is closed to prevent the fuel from leaking out of the branch pipe 1, the valve 11 is arranged in the accommodating groove 42 and is flush with the inner wall of the annular combustion chamber 4, the torsional spring 12 enables the valve 11 to be tightly abutted against the side wall of the accommodating groove 42, and the valve 11 is prevented from accidentally extending into the annular combustion chamber 4 to cause adverse effects on the annular combustion chamber 4 which may be working;
2. when a rotary detonation engine requires ignition: after the rotary detonation engine is started, the electromagnetic valve 31 is opened, fuel is sprayed into the annular combustion chamber 4 by a feeding device of the rotary detonation engine, the electromagnetic valve 31 is controlled by the timing controller 32 to be closed in a delayed mode, the fuel in the annular combustion chamber 4 enters the branch pipe 1 through the through hole 111, waste gas or air in the branch pipe 1 is completely extruded out, the branch pipe 1 is filled with the fuel, then the electromagnetic valve 31 is closed, the ignition unit 2 ignites the fuel in the branch pipe 1, the fuel in the branch pipe 1 is instantaneously combusted to generate deflagration and develops into detonation waves in the branch pipe 1, the valve 11 is pushed by the detonation waves to extend into the annular combustion chamber 4, the detonation waves are transmitted into the annular combustion chamber 4, and most of the detonation waves form initial detonation waves propagating in a single direction in the annular combustion chamber 4, so that the fuel in the annular combustion chamber 4 is detonated.
Example 2
Referring to fig. 4, the present embodiment 2 is different from embodiment 1 in that the branch pipe 1 is arranged to meander along the outer wall of the annular combustion chamber 4, and the side wall of the branch pipe 1 is welded to the outer wall of the annular combustion chamber 4, and when a part of the outer wall of the annular combustion chamber 4 is connected to other components, the branch pipe 1 is arranged to meander along the outer wall of the annular combustion chamber 4.
The principle of embodiment 2 is the same as that of embodiment 1.
Example 3
Referring to fig. 5, the present embodiment 3 is different from embodiment 1 in that the bypass pipe 1 is not provided with the torsion spring 12 and the valve 11 having a plurality of through holes 111, and the bypass pipe 1 is completely communicated with the annular combustion chamber 4.
The implementation principle of embodiment 3 is different from that of embodiment 1 in that: when a rotary detonation engine requires ignition: after the rotary detonation engine is started, the electromagnetic valve 31 is opened, fuel is sprayed into the annular combustion chamber 4 by a feeding device of the rotary detonation engine, the electromagnetic valve 31 is controlled by the time schedule controller 32 to be closed in a delayed mode, the fuel in the annular combustion chamber 4 enters the branch pipe 1 through the opening 41, waste gas or air in the branch pipe 1 is completely extruded out, the branch pipe 1 is filled with the fuel, then the electromagnetic valve 31 is closed, the ignition unit 2 ignites the fuel in the branch pipe 1, the fuel in the branch pipe 1 is instantaneously combusted to generate deflagration, the deflagration waves are developed in the branch pipe 1, the deflagration waves are transmitted into the annular combustion chamber 4, and the fuel in the annular combustion chamber 4 is detonated.
The above embodiments are preferred embodiments of the present application, and the protection scope of the present application is not limited by the above embodiments, so: all equivalent changes made according to the structure, shape and principle of the present application shall be covered by the protection scope of the present application.
Claims (7)
1. The utility model provides a bypass bleed low energy ignition passback formula priming device which characterized in that: the ignition device comprises a branch pipe (1), an ignition unit (2) and a control unit (3), wherein an opening (41) which is communicated with the branch pipe (1) is formed in an annular combustion chamber (4), one end of the branch pipe (1) is communicated with the annular combustion chamber (4), the side wall of the branch pipe (1) is attached to the outer wall of the annular combustion chamber (4), the ignition unit (2) and the control unit (3) are both installed on the branch pipe (1), and the control unit (3) is located on one side, away from the opening (41), of the ignition unit (2) and used for controlling the opening and closing of the branch pipe (1);
be provided with torsional spring (12) and valve (11) on bypass pipe (1), a plurality of through-holes (111) have been seted up in valve (11), valve (11) install in opening (41) department is articulated with annular combustion chamber (4), just the axial setting of annular combustion chamber (4) is followed in articulated shaft (112) of valve (11), torsional spring (12) cover is located on articulated shaft (112).
2. The bypass bleed low energy ignition pass-back initiation device of claim 1, wherein: the branch pipe (1) is wound along the circumferential direction of the outer wall of the annular combustion chamber (4).
3. The bypass bleed low energy ignition pass-back initiation device of claim 1, wherein: the branch pipe (1) is arranged along the outer wall of the annular combustion chamber (4) in a winding mode.
4. A bypass bleed low energy ignition pass-back primer detonator as claimed in claim 1 or 2 or 3 wherein: the control unit (3) comprises an electromagnetic valve (31), and the electromagnetic valve (31) is installed on the branch pipe (1).
5. The bypass bleed low energy ignition pass-back initiation device of claim 4, wherein: the control unit (3) further comprises a time sequence controller (32), and the time sequence controller (32) is connected with the electromagnetic valve (31).
6. The bypass bleed low energy ignition pass-back initiation device of claim 1 or 2 or 3 or 5, wherein: the ignition unit (2) is a spark plug.
7. The bypass bleed low energy ignition pass-back initiation device of claim 1, wherein: an accommodating groove (42) is formed in the side wall of the opening (41), and the valve (11) is arranged in the accommodating groove (42).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110715235.9A CN113756990B (en) | 2021-06-26 | 2021-06-26 | Bypass air-entraining low-energy ignition return type detonating device |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110715235.9A CN113756990B (en) | 2021-06-26 | 2021-06-26 | Bypass air-entraining low-energy ignition return type detonating device |
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| Publication Number | Publication Date |
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| CN113756990A CN113756990A (en) | 2021-12-07 |
| CN113756990B true CN113756990B (en) | 2022-08-05 |
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Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3906720A (en) * | 1965-01-07 | 1975-09-23 | Aerojet General Co | Igniter assembly for rocket motors |
| CN104612821B (en) * | 2015-01-28 | 2017-01-11 | 南京理工大学 | One-way priming device of probing type rotation detonation engine |
| CN106640420B (en) * | 2016-12-30 | 2017-12-29 | 上海洲跃生物科技有限公司 | A kind of pulse-knocking engine of side air inlet |
| CN107013369B (en) * | 2017-04-27 | 2019-04-02 | 江苏大学 | A kind of open and close type rotation unidirectional priming device of detonation engine |
| US11149954B2 (en) * | 2017-10-27 | 2021-10-19 | General Electric Company | Multi-can annular rotating detonation combustor |
| CN109184950B (en) * | 2018-09-25 | 2020-09-01 | 西北工业大学 | Device of low energy ignition initiating detonation wave |
| CN112901344B (en) * | 2021-01-26 | 2022-04-01 | 厦门大学 | Interstage rotary detonation variable-circulation turboshaft engine |
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- 2021-06-26 CN CN202110715235.9A patent/CN113756990B/en active Active
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