CN106134396B - The igniter of oxygen kerosene afterburning cycle engine - Google Patents
The igniter of oxygen kerosene afterburning cycle engineInfo
- Publication number
- CN106134396B CN106134396B CN200910122426.3A CN200910122426A CN106134396B CN 106134396 B CN106134396 B CN 106134396B CN 200910122426 A CN200910122426 A CN 200910122426A CN 106134396 B CN106134396 B CN 106134396B
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- Prior art keywords
- ignition
- igniting
- igniter
- road
- thrust chamber
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Abstract
The present invention discloses a kind of igniter of oxygen kerosene afterburning cycle engine, this device comprises ignition of gas generator road and thrust chamber ignition path, two-way junction is three way type structure, a-road-through gas generator, a-road-through thrust chamber ignition path, another a-road-through igniting agent supply road arranges adjuster and igniter on igniting agent supply road, fill liquid chemic ignition agent in igniter, two ends are sealed by diaphragm; Reversal valve and three grades of throttles are set on thrust chamber ignition path, igniting developing agent storage chamber is set between the two, reversal valve is arranged on ignition of gas generator road and thrust chamber ignition path connectivity part, switch for ignition path, to igniting agent storage chamber filling igniting agent, the total flow of two-way igniting agent filling is by adjuster control, and thrust chamber igniting agent flow is by three grades of throttle controls, and realization is lighted gas generator and thrust chamber with an igniter. There is feature simple in structure, that quality is light, the high fire of reliability steady and nothing is obviously impacted.
Description
Technical field
The present invention relates to igniter technical field, specifically a kind of oxygen kerosene afterburning cycle engineIgniter, can be used for oxygen kerosene engine.
Background technology
Liquid-propellant rocket engine is the core component of carrier rocket. Firing technique is nonhypergolic propellantFirst liquid-propellant rocket engine development needs the key technology solving. The liquid-propellant rocket engine of China's active serviceMainly comprise the liquid oxygen hydrogen engine of hypergolic propellants engine and nonhypergolic propellant. Wherein, spontaneous combustionPropellant engine is without igniting; Two fuel assemblies of the liquid oxygen hydrogen engine of nonhypergolic propellant--thrust chamber and gas generator all will adopt separately independently igniter. At present, China pushes away at nonflammableEnter agent liquid-propellant rocket engine firing technique aspect and there is no disclosing of relevant patent or technical literature.
The nonhypergolic propellant liquid rocket that the former Soviet Union-Russia, the U.S. have developed Multiple Type startsMachine, its firing technique mainly adopts electric igniter or chemic ignition agent. Gas generator and thrust chamber adoptSeparately independently two cover ignition systems. Aspect high thrust motor, there is no and adopt same igniter to realizeThe technology of two fuel assembly igniting, also apply for a patent or disclose in China without correlation technique.
Oxygen kerosene afterburning cycle engine has the advantages such as performance is high, propellant non-toxic inexpensive, is futureThe main development direction of Space Dynamic. Because oxygen kerosene is nonhypergolic propellant, according to the spy of enginePoint, adopts two igniters to be respectively gas generator and thrust chamber igniting according to the conventional method, makesEngine system complexity, architecture quality weight, and reliability is had to impact. If can adopt an ignitingDevice completes the igniting of gas generator and thrust chamber, will address these problems.
Summary of the invention
The technical problem that the present invention solves: in nonhypergolic propellant liquid-propellant rocket engine firing techniqueThe deficiency existing, has researched and developed a kind of igniter of oxygen kerosene afterburning cycle engine, by ignitingThe distribution of agent flux and switching are lighted gas generator and thrust chamber with an igniter simultaneously, make to startMachine system is simple, quality is light, reliability is high.
The technical scheme that the present invention deals with problems: adopt the igniting of aqueous chemical igniting agent, igniting agent is filled with in advanceBe contained in igniter; By reversal valve is set, to control the igniting appearance of a street long-pending, realize engine and adopt a pointFirearm, completes gas generator and thrust chamber igniting; By flow regulator, three grades of throttle controls are setIgniting agent flow processed, carries out gas generator and thrust chamber igniting agent assignment of traffic, guarantees two burning groupsThe reliable ignition of part.
Technical scheme of the present invention is achieved in that the igniter of oxygen kerosene afterburning cycle engineBe provided with ignition of gas generator road and thrust chamber ignition path, gas generator two ignition path junctions are threeFormula, a-road-through gas generator, a-road-through thrust chamber ignition path, another a-road-through igniting agent supplyRoad. On igniting agent supply road, adjuster and igniter are set, fill liquid chemic ignition agent in igniter,Two ends are sealed by diaphragm; Reversal valve and three grades of throttles are set on thrust chamber ignition path, at reversal valve andIgniting developing agent storage chamber is set between three grades of throttles; Reversal valve is arranged on ignition of gas generator road and thrustChamber ignition path connectivity part, switches for ignition path, to igniting agent storage chamber filling igniting agent; Two-way ignitingThe total flow of agent filling is by adjuster control, and thrust chamber igniting agent flow is by three grades of throttle controls.
The present invention had advantages of compared with prior art:
(1) the present invention adopts igniter to replace to realize engine gas with two igniters simultaneously and sends outThe igniting of raw device and thrust chamber is the ignition mode traditional to the oxygen kerosene engine of nonhypergolic propellantImportant breakthrough. Light two combustion mechanisms with an igniter, simplified the ignition structure of engine,Have the advantages that quality is light, reliability is high, for the application of oxygen kerosene afterburning cycle engine has been created excellentGesture.
(2) ignition device structure of the present invention is simple, obvious technical effects, gas generator and thrustSteadily, without obviously impacting, its igniting effect obtains on certain oxygen kerosene afterburning cycle engine in chamber ignitingChecking.
Brief description of the drawings
Fig. 1 oxygen kerosene afterburning of the present invention cycle engine gas generator and thrust chamber igniterSchematic diagram
Detailed description of the invention
Fig. 1 has provided the preferred reality of a kind of oxygen kerosene afterburning cycle engine igniter of the present inventionExecute example, to the further illustrating of embodiment, those skilled in the art of the present technique can be managed in conjunction with the drawingsSeparate and implement the present invention.
In Fig. 1, igniter is provided with ignition of gas generator road and thrust chamber ignition path, at liquidChemic ignition agent supply is provided with adjuster 1, igniter 2 on road. Thrust chamber ignition path is provided with commutation3, three grades of throttles 5 of valve arrange igniting developing agent storage chamber 4 between reversal valve 3 and three grades of throttles 5,For filling the igniting agent distributing from igniter 2.
Oxygen kerosene afterburning cycle engine adopts the igniting of aqueous chemical igniting agent, and aqueous chemical igniting agent fillsFill out at two ends and establish in chaffy igniter 2. Between ignition of gas generator road and thrust chamber ignition pathReversal valve 3 is set, and this valve is two-position three-way valve, in igniting agent stowing operation, and entrance A and outlet CCommunicate, entrance B closes, and igniting agent filling ignition of gas generator road, simultaneously through reversal valve 3 filling pointsFire developing agent storage chamber 4; After filling, reversal valve 3 commutates, and entrance B communicates with outlet C, entrance AClose, two ignition paths work alone; The igniting agent of gas generator is supplied by igniter 2, thrust chamber pointFire agent is supplied by the igniting agent that is filled in the distribution in igniting chamber 4.
The course of work of igniter of the present invention is:
When engine start, adopt the diaphragm of high pressure kerosene (pressure 20～22MPa) extruding igniter 2,Make rupture of diaphragm (fracture pressure 4～7MPa), igniting agent is under the extruding of kerosene, and filling combustion gas occursDevice ignition path, simultaneously through reversal valve 3 filling igniting agent storage chambers 4, the total flow of two-way filling is by regulatingDevice 1 is controlled.
After filling, reversal valve 3 commutates, and two ignition paths start to work alone. Now, combustion gas occursDevice igniting agent flow is controlled by adjuster 1, and thrust chamber igniting agent flow is controlled by three grades of throttles 5. CombustionThe igniting agent of gas generator is supplied by igniter 2, and thrust chamber igniting agent is by the point being filled in igniting chamber 4Fire agent supply. Realize the effect that engine is lighted gas generator and thrust chamber with an igniter simultaneouslyReally.
In order to ensure ignition process thrust chamber igniting stability of flow, the throttle 5 that throttling capacity is very strong is set,This throttle is designed to three grades of throttlings, effectively avoids the cavitation erosion of liquid igniting agent.
Gas generator and thrust chamber temperature reach after the burning-point of liquid oxygen and kerosene, gas generator and thrustThe igniting agent of chamber is progressively substituted by kerosene, and igniting finishes.
The foregoing description of the present embodiment and accompanying drawing have represented preferred version of the present invention, art technology peopleMember can define not departing from the claims in the present invention according to different designing requirements and design parameterScope in carry out various supplements, improvement and replacing, therefore, the present invention is widely.
Claims (2)
1. an igniter for oxygen kerosene afterburning cycle engine, is characterized in that: this device bagDraw together ignition of gas generator road and thrust chamber ignition path, two-way junction is three way type structure, a-road-through combustionGas generator, a-road-through thrust chamber ignition path, another a-road-through igniting agent supply road, on igniting agent supply roadAdjuster (1) and igniter (2) are set, fill liquid chemic ignition agent in igniter (2),Two ends are sealed by diaphragm; Reversal valve (3) and three grades of throttles (5) are set on thrust chamber ignition path,Igniting developing agent storage chamber (4) is set between reversal valve (3) and three grades of throttles (5), reversal valve (3)Be arranged on ignition of gas generator road and thrust chamber ignition path connectivity part, switch for ignition path, to ignitingDeveloping agent storage chamber (4) filling igniting agent, the total flow of two-way igniting agent filling is controlled by adjuster (1),Thrust chamber igniting agent flow is controlled by three grades of throttles (5), and realization is lighted combustion gas with an igniter and sent outRaw device and thrust chamber.
2. the igniter of oxygen kerosene afterburning cycle engine according to claim 1, its spyLevy and be: reversal valve (3) is two-position three-way valve, in igniting agent stowing operation, entrance A and outletC communicates, and entrance B closes, and igniting agent filling ignition of gas generator road, simultaneously through reversal valve (3)The igniting agent storage chamber (4) of filling thrust chamber ignition path; After filling, reversal valve (3) commutation,Entrance B communicates with outlet C, and entrance A closes, and two ignition paths work alone, the igniting of gas generatorAgent is by igniter (2) supply, and thrust chamber igniting agent is by the igniting being filled in igniting agent storage chamber (4)Agent supply.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200910122426.3A CN106134396B (en) | 2009-09-01 | 2009-09-01 | The igniter of oxygen kerosene afterburning cycle engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200910122426.3A CN106134396B (en) | 2009-09-01 | 2009-09-01 | The igniter of oxygen kerosene afterburning cycle engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106134396B true CN106134396B (en) | 2014-06-04 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN200910122426.3A Active CN106134396B (en) | 2009-09-01 | 2009-09-01 | The igniter of oxygen kerosene afterburning cycle engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106134396B (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109113896A (en) * | 2018-08-31 | 2019-01-01 | 西安航天动力研究所 | A kind of small-sized plug-in type chemical ignitor |
| CN110410233A (en) * | 2019-07-23 | 2019-11-05 | 西安航天动力研究所 | Multicomponent packaged type igniter |
| CN111076923A (en) * | 2019-12-18 | 2020-04-28 | 西安航天动力研究所 | Continuous flow calibration system and method for high-temperature gas regulator |
-
2009
- 2009-09-01 CN CN200910122426.3A patent/CN106134396B/en active Active
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109113896A (en) * | 2018-08-31 | 2019-01-01 | 西安航天动力研究所 | A kind of small-sized plug-in type chemical ignitor |
| CN109113896B (en) * | 2018-08-31 | 2024-02-06 | 西安航天动力研究所 | Small plug-in type chemical igniter |
| CN110410233A (en) * | 2019-07-23 | 2019-11-05 | 西安航天动力研究所 | Multicomponent packaged type igniter |
| CN110410233B (en) * | 2019-07-23 | 2020-08-18 | 西安航天动力研究所 | Multi-component packaging type igniter |
| CN111076923A (en) * | 2019-12-18 | 2020-04-28 | 西安航天动力研究所 | Continuous flow calibration system and method for high-temperature gas regulator |
| CN111076923B (en) * | 2019-12-18 | 2021-07-20 | 西安航天动力研究所 | Continuous flow calibration system and method for high-temperature gas regulator |
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| GR03 | Grant of secret patent right | ||
| GRSP | Grant of secret patent right | ||
| DC01 | Secret patent status has been lifted | ||
| DCSP | Declassification of secret patent |