CN104234870B - The coaxial pintle formula ejector filler thrust chamber of a kind of fluting - Google Patents
The coaxial pintle formula ejector filler thrust chamber of a kind of fluting Download PDFInfo
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- CN104234870B CN104234870B CN201410264384.8A CN201410264384A CN104234870B CN 104234870 B CN104234870 B CN 104234870B CN 201410264384 A CN201410264384 A CN 201410264384A CN 104234870 B CN104234870 B CN 104234870B
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- central tube
- ejector filler
- fluting
- inner sleeve
- housing
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Abstract
The present invention relates to the coaxial pintle formula ejector filler thrust chamber of a kind of fluting. Comprise central tube and housing, between central tube and housing, be also provided with inner sleeve and outer sleeve; Outer sleeve and housing form outer ring passage and nozzle ring; Inner sleeve and central tube form central passage and radial nozzles; Outer sleeve upper end is connected with central tube with gasket ring by main spring; Inner sleeve upper end is connected with central tube with gasket ring by auxiliary spring. The invention provides a kind of high efficiency, the coaxial pintle formula of fluting ejector filler thrust chamber that cost is low.
Description
Technical field
The invention belongs to liquid-propellant rocket engine field, relate to one without liquid film Cooling Thrust Chamber,Relate in particular to the coaxial pintle formula ejector filler thrust chamber of a kind of fluting. Can be used for high thrust, high constant pressure,The liquid rocket rail control engine of fast-response.
Background technology
Under the situation of China's military aerospace device high speed development, improve existing liquid rail control rocketEngine ability is very urgent, and this requires rail control engine to possess fast-response, high-performance, lightweightChange ability. Because technical difficulty is large, at present domestic also fail to develop the response time be less than 30ms,The conventional liq rail control engine that thrust ten thousand Ns of levels, thrust-mass ratios are greater than 500.
Traditional liquid-propellant rocket engine ejector filler as Orifice Injector centrifugal injector andPintle formula ejector filler be apply early, more spray form, its relies on ejector filler outer ring to adoptSpecial Cooling Holes is realized the low temperature control in border area, taking into account under stability and cooling condition,Obtain rational performance. Under some mission requirements, due to inlet pressure and repeatedly start, ringRestriction between seasonable, rail appearance control liquid-propellant rocket engine generally adopts high temperature resistant niobium alloy spoke at presentPenetrate cooling scheme, the optimal selection of thrust chamber body portion remains the cooling niobium alloy of radiation and ceramic baseComposite body portion.
For Thrust chamber with Radiation Cooling, need special liquid film cooling, by higher proportionLiquid film is arranged near wall region, makes combustibility cannot reach the highest, and while starting in addition, liquid film is coldBut propellant residual when chamber needs filling and shutdown slowly flows, and causes engine responsePoor. Traditional pintle formula ejector filler outer ring propellant and inner ring propellant are with the form of annular liquid filmClash into, mix on pintle top, it is less that rear space Mixed Zone is clashed in this spray, spyBe not in the time that propellant flow rate is larger, very difficult formation is radially mixing ratio distribution preferably, Wu FayouEffect realizes performance and cooling taking into account.
Owing to relying on ejector filler organizationally efficiently to burn, reach reliable by impinging jet optimization againThe target of cooling body portion, thereby technical difficulty is larger. Push away greatly in order to realize current rail control engineThe high performance target of power fast-response, has developed the two of the special cooling fluting spray structure of a kind of nothingSleeve " face shutdown " pintle formula thrust chamber structure. Adopt the Central Fuel fluting scheme of two sleevesMake center propellant with pencil jet and outer ring propellant liquid film colliding, not only increase fuel withOxidant contact area, has strengthened jet partial penetration ability, and part pencil jet is more heldEasily penetrate outer ring liquid film, the various flows that forms on space (radially with axially) is strong, mix scoreThe synthesizing jet-flow that cloth irregular is staggered, firing angle is different is for can effectively reduce border area temperature.
Summary of the invention
In order to solve existing technical problem in background technology, the present invention proposes a kind of flutingCoaxial pintle formula ejector filler thrust chamber.
Technical scheme of the present invention is: the coaxial pintle formula ejector filler thrust chamber of a kind of fluting, its spyDifferent part is: comprise central tube and housing, be also provided with inner sleeve between central tube and housingWith outer sleeve;
Above-mentioned outer sleeve and housing form outer ring passage and nozzle ring;
Above-mentioned inner sleeve and central tube form central passage and radial nozzles;
Above-mentioned outer sleeve upper end is connected with central tube by main spring, gasket ring;
Above-mentioned inner sleeve upper end is connected with central tube by auxiliary spring, gasket ring;
Above-mentioned central tube lower end is provided with termination notch; Termination notch is made up of major trough and auxiliary groove;
Above-mentioned major trough height is higher than auxiliary groove, and auxiliary well width is wider than major trough.
Advantage of the present invention is: 1. thrust chamber of the present invention is owing to adopting without the independent cooling knot of liquid filmStructure, the independent sealed structure of two sleeves, high rigidity, large deformation special type spring, simple in structure, gramTaken conventional rail attitude control engine because the cooling response characteristic of bringing of liquid film is poor separately, performance is on the low sideProblem, realized the quick response of high thrust motor, the response time is by original hundreds of millisForeshorten to 30ms second.
2. ejector filler of the present invention adopts Central Fuel fluting pintle formula spray form, innovative designThe narrow major trough structure of novel height, makes center propellant hit with pencil jet and outer ring propellant liquid filmHit, not only increase fuel and oxidant contact area, strengthened jet partial penetration ability, makeObtain part pencil jet and more easily penetrate outer ring liquid film. By short wide auxiliary groove optimization mixing scoreCloth, has formed on space the irregular phase that various flows is strong, mixing ratio distributes of (radially with axially)Wrong, the different synthesizing jet-flow of firing angle, thus combustibility is improved greatly, and efficiency of combustion canReach 0.97.
3. the present invention adopts the narrow major trough structure of novel height, and enhanced fuel jet makes part combustionMaterial penetrates outer ring oxidant cooled inner wall, and optimize mixing ratio by short wide auxiliary groove and distribute, andGuide plate with angle is set, has reduced the effect that splashes when jet hits wall after shock, and made moreMany fuel-rich spray fans flow down, and have effectively controlled body portion wall temperature lower than 1300 DEG C, have realized and having pushed awayThe power chamber long-life is reliably cooling.
4. ejector filler structural design of the present invention is simple, and processing parts quantity is few, technique is simple, toolHave response fast, efficiency advantages of higher, has a extensive future, and is particularly useful for high thrust, high chamberThe rail control engine of pressure, fast-response.
Brief description of the drawings
Fig. 1 is structural representation of the present invention;
Fig. 2 is thrust chamber control chamber effort formation schematic diagram of the present invention;
Fig. 3 is ejector filler of the present invention outer ring and center flow channels/hermetically-sealed construction profile;
Fig. 4 is central tube end tank mouth longitudinal section view of the present invention;
Wherein 1-housing, 2-outer sleeve, 3-hydraulic control chamber, 4-inner sleeve, 5-main spring,6-auxiliary spring, 7-central tube, 8-gasket ring, 9-deflector, 10-spatter plate, 11-center-pole, 12-Central passage, 13-radial nozzles, 14-outer ring passage, 15-nozzle ring, 16-termination notch,17-pintle head.
Detailed description of the invention
Referring to Fig. 1-4, the present invention is the coaxial pintle formula ejector filler thrust chamber of a kind of fluting, comprisesCentral tube 7 and housing 1, be also provided with inner sleeve 4 and overcoat between central tube 7 and housing 1Cylinder 2; Outer sleeve 2 forms outer ring passage 14 and nozzle ring 15 with housing 1; Inner sleeve 4Form central passage and radial nozzles with central tube 7; Outer sleeve 2 upper ends by main spring 5,Gasket ring 8 is connected with central tube 7; Inner sleeve 4 upper ends are by auxiliary spring 6, gasket ring 8 and centerCylinder 7 is connected; Central tube 7 lower ends are provided with termination notch 16; Termination notch 16 by major trough andAuxiliary groove forms; Major trough height is higher than auxiliary groove, and auxiliary well width is wider than major trough.
Fig. 1 has provided of the present invention a kind of without the cooling thrust chamber structural principle of special liquid film, figure2 have provided the structural principle of ejector filler start control starting and shutdown, and Fig. 3 has provided propellantThe structural representation of spray and sealing, Fig. 4 has provided the arrangement of slotting on center part termination and has shownIntention, makes those skilled in the art of the present technique can understand enforcement the present invention.
In Fig. 1 and Fig. 2, in " face shutdown " ejector filler, highly pressurised liquid actuating system is setWith high rigidity large deformation special type spring, two sleeve seal structures, comprise that ejector filler housing 1 is with outerThe hydraulic control chamber 3 that sleeve 2 forms, inner sleeve 4, main spring 5, auxiliary spring 6, central tube7, for adjusting the gasket ring 8 of pre compressed magnitude, for adjusting the pad of outer sleeve 2 and inner sleeve 4Sheet, when starting, high pressure propellant enters high pressure chest, and its effect outer sleeve 2 that is used as power moves upward,Sealing place of opening outer sleeve 2 and inner sleeve 4, two-way propellant sprays into combustion chamber 9, clashes intoAfter on plate 10, form the cooling body of the fuel-rich jet of low temperature portion spattering. When shutdown, high pressure chest is closed alsoDischarge, outer sleeve 2 and inner sleeve 4 move downward under spring-force driven dual and to realize spray face closeEnvelope.
In Fig. 3, center-pole 11 and central tube 7 form central passage 12, have realized differenceThe radially spray of notching construction, the narrow major trough of height of different structure and short is processed in central tube 7 lower endsWide auxiliary groove, and form radial nozzles 13 with center-pole 11, fuel is by central passage 12, footpathForm the radial radial jet of multiply to nozzle 13, spurt in combustion chamber 9. Inner sleeveThe plane of 4 lower end and center-pole 11 forms central plane sealing place under auxiliary spring 6 effects,The high rigidity adopting, the special type spring of large deformation have met high thrust motor spray stroke and sprayHole sealing.
In Fig. 3, form outer ring passage 14 at ejector filler housing 1 and outer sleeve 2, this is outer(spray face, also can be at main bullet for the outlet of circle passage 14 and outer sleeve 2 looping nozzles 15Under the effect of spring 4, form outer ring conical surface seal), oxidant flows to annular by outer ring passage 14Nozzle 15 sprays in combustion chamber 9, forms mobile vertically annular along outer sleeve 2 outer mold surfaceJet, and circumferentially distribute with uniform speed.
As shown in Figure 3, outer sleeve 2 of the present invention can be large according to the desired thrust of engineThe spray diameter that little design is different and spray angle realize the adjustment of spray area, central tube 7Termination notch 16 can be according to the different narrow major trough of height of engine desired thrust size designRealize the adjustment of spray area with short wide auxiliary groove, meet the injection pressure drop (speed) of design. OutwardThe motion of sleeve 2 and inner sleeve 4 is realized by the effect of high hydraulic coupling, and what the present invention adopted is liquidPressure is opened the mode of closing with spring force.
Main spring 5 of the present invention, auxiliary spring 6 can be according to required sealing initial pretightning force,Pre compressed magnitude and work total kilometres design, and realize by width and the thickness of adjusting variable shaped beamRequired spring rate.
The termination notch 16 of central tube 7 of the present invention at least provides following a kind of preferred embodiment,In the thrust range of design, can amplify in proportion, the performance reaching is substantially irrelevant with thrust.In the time doing large change in size (high thrust design), only need to make minimum change and just can reachTo desired performance and locular wall compatibility, realize thrust chamber special liquid film condition be not setUnder reliable border area cooling.
The termination of center-pole 11 of the present invention is provided with niobium alloy material with ORCPintle head 17 can be resisted high temperature reflux combustion gas,
Embodiment mono-
Central tube 7 is as Figure 1 and Figure 4 one of vital parts of embodiment, centerCylinder 7 termination notch 16 for interval evenly, vary in size, staggered T-shaped groove and squareShape groove, its T-shaped groove 13 is major trough, rectangular channel 14 is auxiliary groove, sprays from radial nozzles 13Hitting of the axial outer ring annular liquid film that the radial radial jet of multiply and nozzle ring 15 sprayHit, ensure to form the good radially mixing score that has larger gradient after two strands of propellants clash intoCloth, had not only raised the efficiency but also can realize the abundant cooling body of the part of fuel penetrating portion. Part streams existsClash into and click after wall, flow along spattering plate 9 surfaces. Notch design is according to blocking rate, auxiliary groove ratioExample and groove number, injection pressure drop are optimized than (or ratio of momentum), pintle diameter etc.
Embodiment bis-
Main spring 5, auxiliary spring 6 is one of vital parts of embodiment, adopts 65Mn bulletSpring steel is through heat treatment, line cutting, surface treatment and suppress the processes such as processing, meets design requirementHigh spring rate and large decrement. When shutdown, rely on precompressed pretightning force to make outer sleeve2 and inner sleeve 4 in sealing state.
Embodiment tri-
As Figure 1 and Figure 4, the termination notch 16 of central tube 7 is that interval is even, big or smallDifferent, staggered T-shaped groove and rectangular channel, its T-shaped groove 13 is major trough, rectangular channel 14Be auxiliary groove, spray the radial radial jet of multiply and nozzle ring 15 sprays from radial nozzles 13The shock of axial outer ring annular liquid film, ensures two strands of propellants clash into after good the having of formationThe radially mixing ratio of large gradient distributes, and has not only raised the efficiency but also to realize the part of fuel penetrating abundantCooling body portion. Part streams is clashing into after click wall, flows along spattering plate 9 surfaces.
The foregoing description of the present embodiment and accompanying drawing have represented preferred version of the present invention, art technology peopleMember can not depart from the claims in the present invention institute according to different designing requirements and design parameterIn the scope defining, carry out various supplements, improvement and replacing, therefore, the present invention is widely.
Claims (1)
1. the coaxial pintle formula ejector filler thrust chamber of fluting, is characterized in that: comprise central tubeWith housing, between central tube and housing, be also provided with inner sleeve and outer sleeve;
Described outer sleeve and housing form outer ring passage and nozzle ring;
Described inner sleeve and central tube form central passage and radial nozzles;
Described outer sleeve upper end is connected with central tube with gasket ring by main spring;
Described inner sleeve upper end is connected with central tube with gasket ring by auxiliary spring;
Described central tube lower end is provided with termination notch; Termination notch is made up of major trough and auxiliary groove;Described major trough height is higher than auxiliary groove, and auxiliary well width is wider than major trough.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410264384.8A CN104234870B (en) | 2014-06-13 | 2014-06-13 | The coaxial pintle formula ejector filler thrust chamber of a kind of fluting |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201410264384.8A CN104234870B (en) | 2014-06-13 | 2014-06-13 | The coaxial pintle formula ejector filler thrust chamber of a kind of fluting |
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| CN104234870A CN104234870A (en) | 2014-12-24 |
| CN104234870B true CN104234870B (en) | 2016-05-18 |
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| CN108286478B (en) * | 2017-12-20 | 2019-07-12 | 北京控制工程研究所 | A kind of pre- rotating pintle ejector filler applied to double elements liquid-propellant rocket engine |
| CN109506941B (en) * | 2018-11-20 | 2020-07-14 | 西安航天动力技术研究所 | Variable thrust mechanism opening reliability growth test device of yaw pitching engine |
| CN110500201B (en) * | 2019-07-31 | 2021-01-12 | 西安航天动力研究所 | Head structure of inclined groove type pintle injector |
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| CN112431693B (en) * | 2020-11-19 | 2021-11-30 | 北京航空航天大学 | Pin injector, rocket engine and rocket |
| CN112502857B (en) * | 2020-12-02 | 2022-02-22 | 中国人民解放军国防科技大学 | Pintle injector and liquid rocket engine |
| CN112324589B (en) * | 2020-12-02 | 2021-09-24 | 中国人民解放军国防科技大学 | Pintle injector and liquid rocket engine with same |
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| CN115263605B (en) * | 2022-09-28 | 2023-03-03 | 北京星河动力装备科技有限公司 | Pintle injector, rocket motor and liquid rocket |
| CN117072346A (en) * | 2023-10-17 | 2023-11-17 | 沈阳航天新光集团有限公司 | Device for connecting combustion chamber and injector in thrust chamber |
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