CN105020051A - Combustor acoustics research device - Google Patents
Combustor acoustics research device Download PDFInfo
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- CN105020051A CN105020051A CN201510347545.4A CN201510347545A CN105020051A CN 105020051 A CN105020051 A CN 105020051A CN 201510347545 A CN201510347545 A CN 201510347545A CN 105020051 A CN105020051 A CN 105020051A
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Abstract
The invention discloses a combustor acoustics research device. The combustor acoustics research device comprises a propellant pulse supply device, a combustor and a continuous combustor length adjusting device. The propellant pulse supply device comprises a rack, an electric pulser, a connecting rod, a lower bend, a rigid straight pipe and an upper bend. The continuous combustor length adjusting device comprises a water pressure pipeline and a sliding injector which are arranged inside the combustor. The sliding injector comprises a sliding sleeve, an oxygen pipe and a fuel cavity. The sliding sleeve comprises a cone-shaped head and a hollow guiding sliding rod. The guiding sliding rod is internally provided with a propellant supply pipeline connected with the upper bend. The lower bend is connected with a liquid-state propellant source. after the structure is adopted, the pulse supply can be achieved on a propellant in the combustor, and the real supply pulse can be simulated. In addition, due to the pulse supply of the propellant, the acoustics vibration in various modes in the combustor can be stimulated, and therefore the influence of various kinds of acoustics vibration on the combustion stability of an engine can be researched.
Description
Technical field
The application relates to a kind of liquid oscilaltion device, particularly a kind of firing chamber acoustic investigation device, for investigating the impact of vibration on engine combustion stability.
Background technique
Along with the more and more fierce enhancing realized with people of competition is explored in space flight, in the urgent need to research New high-thrust rocket motor.Rocket motor development is a great systems engineering, can run into many difficulties in development process, and wherein unstability burning is impassable key subjects.
Because the complexity of rough burning generally will consider flameholding sexual factor in the reseach of engine primary stage.Existing theory also cannot explain the mechanism of production of rough burning completely, needs the stability assessment being completed motor by verification experimental verification.
Motor rough burning to affect influence factor numerous, vibration is exactly one of them important influence factor.But, also there is no special testing apparatus at present, be used for studying the impact of vibration on engine combustion stability.
application content
The technical problem that the application will solve is for above-mentioned the deficiencies in the prior art, and a kind of firing chamber acoustic investigation device is provided, this firing chamber acoustic investigation device is by supplying propellant agent pulsation, excite the acoustic oscillations in firing chamber, thus be used for studying the impact of vibration on engine combustion stability.
For solving the problems of the technologies described above, the technological scheme that the application adopts is:
A kind of firing chamber acoustic investigation device, comprises propellant agent pulsation supplier, firing chamber and chamber length continuous regulating mechanism;
Described propellant agent pulsation supplier comprises stand, the electric pulse device be fixed on stand base plate, be vertically installed in electric pulse device top connecting rod, be fixedly installed on connecting rod top lower elbow, be fixedly installed on the rigid straight pipe on lower elbow top, be fixedly installed on the upper elbow on rigid straight pipe top;
The slip driven unit that described chamber length continuous regulating mechanism comprises slip ejector filler and slip ejector filler can be driven to move axially along firing chamber; Described slip ejector filler is arranged in firing chamber, and firing chamber is divided into zone of combustion and non-burning district.
Described slip ejector filler comprises flip sleeve, oxygen hose, flinger ring and fuel cavity.
Described flip sleeve comprises and can seal the guiding slide bar of conical nose and the hollow be slidably matched with Inner Wall of Combustion Chamber.
Described conical nose and oxygen hose are sealedly and fixedly connected, and form oxygen chamber; The front end in oxygen chamber is disposed with described flinger ring and fuel cavity; Circular hole on described fuel cavity, oxygen hose forms the nozzle arrangements pointing to zone of combustion together with flinger ring.
Described guiding slide bar passes and is connected with the slipper seal of rear side end cap from the rear side end cap of firing chamber; Described guiding slide bar is built-in with propellant feed pipeline.
Described lower elbow is connected with liquid propellant source, and upper elbow is connected with described propellant feed pipeline.
Described slip driven unit is the water pressure pipeline be arranged in firing chamber in non-burning district.
A free end of described lower elbow is connected with propellant source by bottom hose, and a free end of upper elbow is connected with the propellant feed pipeline in described guiding slide bar by top hose.
Described firing chamber is also connected with cooling unit, this cooling unit comprises cooling inner core, cooling sandwith layer and cooling jacket, and wherein, cooling inner core is fixedly connected with the front side end cap of firing chamber, cooling sandwith layer matches with cooling inner core, and cooling jacket is set in the periphery of cooling sandwith layer; Described cooling jacket is provided with cooling water inlet and coolant outlet.
The internal diameter of described rigid straight pipe depends on the speed that propellant agent flows, and the speed of propellant agent flowing is no more than 12m/s.
Described electric pulse device is variable-frequency pulse device.
The length of described rigid straight pipe depends on the pulse amplitude of electric pulse device and the compressibility of propellant agent.
The pulse wavelength that the length of described rigid straight pipe sends than electric pulse device is little more than 10 times.
Described upper elbow and lower elbow are right-angle elbow pipe.
Described electric pulse device, connecting rod and rigid straight pipe are coaxial setting.
After the application adopts said structure, there is following beneficial effect:
1. the setting of above-mentioned propellant agent pulsation supplier, can make the propellant agent in firing chamber realize pulsation supply, can supply pulsation that is virtually reality like reality.In addition, the pulsation supply of this propellant agent, can excite the acoustic oscillations of the various mode in firing chamber, thus can be used for studying the impact of various acoustic oscillations on engine combustion stability.
2. the setting of above-mentioned chamber length continuous regulating mechanism, can make the variable-length of firing chamber, by short elongated or shortened by long, and is consecutive variations; Can be used in studying the length consecutive variations due to firing chamber, the consecutive variations of caused firing chamber acoustic mode is on the impact of combustion stability, along with the consecutive variations of firing chamber, various acoustic mode can be simulated in firing chamber, and be consecutive variations, such as when Actual combustion room length is long by minor face, acoustic mode in firing chamber by the tangential and single order Longitudinal data mode transformation to single order of the tangential acoustic mode in single rank, then can become the acoustic mode of higher order until single order longitudinal mode; When Actual combustion room length is by long shortening, the change of acoustic mode is just in time contrary, so can simulate the various acoustic oscillations conditions run in true firing chamber, for investigating the combustion stability of ejector filler structural type and even whole motor.By structural type and even the layout type of the nozzle on change slip ejector filler, thus obtain the good ejector filler of stability and even engine structure.
Accompanying drawing explanation
Fig. 1 shows the structural representation of a kind of firing chamber of the application acoustic investigation device;
Fig. 2 shows the structural representation of propellant agent pulsation supplier in the application;
Fig. 3 shows the detonation configuration schematic diagram of firing chamber and chamber length continuous regulating mechanism in the application;
Fig. 4 shows the perspective view of firing chamber and chamber length continuous regulating mechanism in the application;
Fig. 5 shows the vertical section structure schematic diagram of firing chamber and chamber length continuous regulating mechanism in application;
Fig. 6 shows the perspective side structural representation of flip sleeve in application;
Fig. 7 shows the left TV structure schematic diagram of the solid of flip sleeve in the application
Fig. 8 shows the structural representation of stand in the application;
Fig. 9 shows the structural representation of electric pulse device in the application;
Figure 10 shows the structural representation of connecting rod in the application;
Figure 11 shows the structural representation of upper elbow or lower elbow in the application;
Figure 12 shows the structural representation of rigid straight pipe in the application.
Wherein have: 1. electric pulse device; 2. connecting rod; 3. descend elbow; 4. bottom hose; 5. rigid straight pipe; 6. go up elbow; 7. top hose; 8. stand; 9. connecting rod interface; 10. straight tube slip circular hole; 11. tapped holes; 12. firing chambers; 13. slip ejector fillers; 14. flip sleeves; 141. conical nose; 142. guiding slide bars; 143. propellant agent entrances; 144. oxygen entrances; 15. oxygen hoses; 16. flinger rings; 17. fuel cavity; 18. sliding rings; 19. hydraulic pressure water inlets; 20. hydraulic pressure water outs; 21. cooling inner cores; 22. cooling sandwith layers; 23. cooling jackets; 231. cooling water inlet; 232. coolant outlet; 24. bolts; 25. propellant agent pulsation supplieies.
Embodiment
Below in conjunction with accompanying drawing and concrete better embodiment, the application is described in further detail.
As shown in Figure 1, a kind of firing chamber acoustic investigation device, comprises propellant agent pulsation supplier 25, firing chamber 12 and chamber length continuous regulating mechanism.
As shown in Figure 2, above-mentioned propellant agent pulsation supplier 25 comprises electric pulse device 1, connecting rod 2, lower elbow 3, bottom hose 4, rigid straight pipe 5, upper elbow 6, top hose 7 and stand 8.
The structure of above-mentioned stand 8 as shown in Figure 8, the intermediate support plate comprising stand base plate, stand top board and be arranged between the two.The center of stand base plate is provided with several tapped holes 11, and the center of stand top board and intermediate support plate is provided with a straight-bar slip circular hole 10.Stand 8 requires rigidity and has good stability, and its eigentone much larger than the propellant agent impulse hunting frequency that will realize, must reduce the impact on the oscillation of flows that will trigger.
As shown in Figure 9, be fixed in the tapped hole 11 of stand base plate by screw by electric pulse device 1, electric pulse device 1 is preferably variable-frequency pulse device to the structure of above-mentioned electric pulse device 1.
The structure of above-mentioned connecting rod 2 as shown in Figure 10, is vertically installed in the top of electric pulse device 1.Connecting rod 2 need select the material that light rigidity is good, to make its quality negligible.
The structure of above-mentioned upper elbow 6 and lower elbow 3 as shown in figure 11, is all preferably right-angle elbow pipe, all has two free ends, be respectively vertical free end and horizontal free end.Wherein, the bottom corners place of lower elbow 3 is provided with a connecting rod interface 9, and this connecting rod interface 9 matches with the top of connecting rod 2, makes lower elbow 3 be fixedly connected on the top of connecting rod 2.
The vertical free end of lower elbow 3 can pass from the straight-bar slip circular hole 10 of intermediate support plate, and is fixedly connected with the bottom of rigid straight pipe 5; The horizontal free end of lower elbow 3 is fixedly connected with bottom hose 4.
The vertical free end of upper elbow 6 can pass from the straight-bar slip circular hole 10 of stand top board, and is fixedly connected with the top of rigid straight pipe 5; The horizontal free end of upper elbow 6 is preferably fixedly connected with top hose 7.
As shown in figure 12, rigid straight pipe 5 is vertically arranged the structure of rigid straight pipe 5, and electric pulse device 1, connecting rod 2 and rigid straight pipe 5 are coaxial setting.Rigid straight pipe 5 requires that rigidity self as far as possible gently, is also that specific stiffness wants high, the inertia effects that reduction is vibrated as far as possible greatly.
The liquid that can flow all is had, the propellant agent namely in the application in top hose 7, upper elbow 6, rigid straight pipe 5, lower elbow 3 and bottom hose 4.The internal diameter of rigid straight pipe 5 depends on the speed that aforesaid liquid flows, and the rate request of flow of fluid is no more than 12m/s.The length of rigid straight pipe 5 depends on the pulse amplitude of electric pulse device 1 and the compressibility of liquid.The pulse wavelength that the length of rigid straight pipe 5 preferably sends than electric pulse device 1 is little more than 10 times.At this moment, can think the liquid of rigid straight pipe 5 inside, namely propellant agent is a rigid body.
The slip driven unit that above-mentioned chamber length continuous regulating mechanism comprises slip ejector filler 13 and slip ejector filler 13 can be driven to move axially along firing chamber 12.
As shown in Fig. 3, Fig. 4 and Fig. 5, above-mentioned slip ejector filler 13 is arranged in firing chamber 12, and firing chamber 12 is divided into zone of combustion and non-burning district.
Above-mentioned slip ejector filler 13 comprises flip sleeve 14, oxygen hose 15, fuel cavity 17 and is arranged on oxygen hose 15 and fuel cavity 17 flinger ring 16 between the two.
As shown in Figure 6 and Figure 7, above-mentioned flip sleeve 14 comprises one and to be arranged in firing chamber 12 and the guiding slide bar 142 of the conical nose 141 be slidably matched with firing chamber 12 inner wall sealing and a hollow.
As shown in Figure 3, between conical nose 141 and firing chamber 12 inwall, be provided with a sliding ring 18, thus slipper seal between the two can be ensured.
Above-mentioned oxygen hose 15 and fuel cavity 17 fix with conical nose 141 successively.
Above-mentioned conical nose 141 is sealedly and fixedly connected with oxygen hose 15, forms oxygen chamber; The front end in oxygen chamber is disposed with above-mentioned flinger ring 16 and fuel cavity 17.
Circular hole on above-mentioned fuel cavity 17, oxygen hose 15 forms the nozzle arrangements pointing to zone of combustion together with flinger ring 16.The type of this nozzle arrangements and distribution mode can change as required, also can be single nozzles.
Above-mentioned guiding slide bar 142 on slip ejector filler 13 passes and is connected with the slipper seal of rear side end cap from the rear side end cap of firing chamber 12.Preferably, be also provided with a sliding ring 18 between end cap on rear side of lead slide bar 142 and firing chamber 12, thus slipper seal between the two can be ensured.
Be provided with propellant feed pipeline and oxygen entrance 144 in the cavity of above-mentioned guiding slide bar 142, this oxygen entrance 144 is connected with oxygen hose 15.The entrance of propellant feed pipeline, is also propellant agent entrance 143.
As shown in Figure 3, above-mentioned slip driven unit is preferably arranged on the water pressure pipeline in firing chamber 12 in non-burning district, but can be also other driven unit, as cylinder etc.
Water pressure pipeline comprises and is arranged at the water pressure entrance 19 and water pressure outlet 20 that firing chamber 12 rear side end covers.Water pressure pipeline also can play the effect of cooling to firing chamber 12.
When slip driven unit adopts water pressure pipeline, the principle of chamber length continuous regulating mechanism length adjustment is as follows:
Moving axially of above-mentioned slip ejector filler 13, mainly due to slip ejector filler 13 both sides, be also that the pressure difference in zone of combustion and non-burning district causes, the effect of water pressure pipeline mesohigh water is exactly punching press and decompression.When being filled with high pressure water in non-burning district, non-burning district pressure increase, and zone of combustion pressure is constant, non-burning district pressure is caused to be greater than zone of combustion pressure, thus promotion slip ejector filler 13 moves to direction, zone of combustion (being also the left side shown in Fig. 5), makes the physical length of firing chamber 12 shorten.Otherwise when sluicing from non-burning district, process is just in time contrary, makes slip ejector filler 13 move to the direction away from zone of combustion, makes the length of Actual combustion room 12.
A free end of above-mentioned lower elbow 3 is connected with liquid propellant source preferably by bottom hose 4, and a free end of upper elbow 6 is connected with the propellant agent entrance 143 in guiding slide bar 142 preferably by top hose 7.
Propellant feed pipeline in above-mentioned bottom hose 4, lower elbow 3, rigid straight pipe 5, upper elbow 6, top hose 7 and guiding slide bar 142, the whole propellant feed pipeline of common composition.
The flexibility needs of above-mentioned bottom hose 4 and top hose 7 are enough good, to such an extent as to can ignore its impact of vibration on triggered Pulsating Flow.
Above-mentioned firing chamber 12 is also connected with cooling unit, and this cooling unit comprises cooling inner core 21, cooling sandwith layer 22 and cooling jacket 23.
Wherein, cooling inner core 21 is fixedly connected with the front side end cap of firing chamber 12, is fixedly connected with preferably by bolt 24.
Cooling sandwith layer 22 matches with cooling inner core 21, and cooling jacket 23 is set in the periphery of cooling sandwith layer 22; Cooling jacket 23 is provided with cooling water inlet 231 and coolant outlet 232.
The working principle of propellant agent pulsation supplier is: electric pulse device 1 starts, drive above-mentioned whole propellant feed pipeline vibration, and propellant agent in whole propellant feed pipeline is due to the inertia of self, thus make its flow produce vibration, realize the pulsation supply of propellant agent in the application.
More than describe the preferred implementation of the application in detail; but the application is not limited to the detail in above-mentioned mode of execution, within the scope of the technical conceive of the application; can carry out multiple equivalents to the technological scheme of the application, these equivalents all belong to the protection domain of the application.
Claims (10)
1. a firing chamber acoustic investigation device, is characterized in that: comprise propellant agent pulsation supplier, firing chamber and chamber length continuous regulating mechanism;
Described propellant agent pulsation supplier comprises stand, the electric pulse device be fixed on stand base plate, be vertically installed in electric pulse device top connecting rod, be fixedly installed on connecting rod top lower elbow, be fixedly installed on the rigid straight pipe on lower elbow top, be fixedly installed on the upper elbow on rigid straight pipe top;
The slip driven unit that described chamber length continuous regulating mechanism comprises slip ejector filler and slip ejector filler can be driven to move axially along firing chamber; Described slip ejector filler is arranged in firing chamber, and firing chamber is divided into zone of combustion and non-burning district;
Described slip ejector filler comprises flip sleeve, oxygen hose, flinger ring and fuel cavity;
Described flip sleeve comprises and can seal the guiding slide bar of conical nose and the hollow be slidably matched with Inner Wall of Combustion Chamber;
Described conical nose and oxygen hose are sealedly and fixedly connected, and form oxygen chamber; The front end in oxygen chamber is disposed with described flinger ring and fuel cavity; Circular hole on described fuel cavity, oxygen hose forms the nozzle arrangements pointing to zone of combustion together with flinger ring;
Described guiding slide bar passes and is connected with the slipper seal of rear side end cap from the rear side end cap of firing chamber; Described guiding slide bar is built-in with propellant feed pipeline;
Described lower elbow is connected with liquid propellant source, and upper elbow is connected with described propellant feed pipeline.
2. firing chamber according to claim 1 acoustic investigation device, is characterized in that: described slip driven unit is the water pressure pipeline be arranged in firing chamber in non-burning district.
3. firing chamber according to claim 1 acoustic investigation device, it is characterized in that: a free end of described lower elbow is connected with propellant source by bottom hose, a free end of upper elbow is connected with the propellant feed pipeline in described guiding slide bar by top hose.
4. firing chamber according to claim 1 acoustic investigation device, it is characterized in that: described firing chamber is also connected with cooling unit, this cooling unit comprises cooling inner core, cooling sandwith layer and cooling jacket, wherein, cooling inner core is fixedly connected with the front side end cap of firing chamber, cooling sandwith layer matches with cooling inner core, and cooling jacket is set in the periphery of cooling sandwith layer; Described cooling jacket is provided with cooling water inlet and coolant outlet.
5. firing chamber according to claim 1 acoustic investigation device, is characterized in that: the internal diameter of described rigid straight pipe depends on the speed that propellant agent flows, and the speed of propellant agent flowing is no more than 12m/s.
6. firing chamber according to claim 1 acoustic investigation device, is characterized in that: described electric pulse device is variable-frequency pulse device.
7. firing chamber acoustic investigation device according to claim 1 or 5, is characterized in that: the length of described rigid straight pipe depends on the pulse amplitude of electric pulse device and the compressibility of propellant agent.
8. firing chamber according to claim 7 acoustic investigation device, is characterized in that: the pulse wavelength that the length of described rigid straight pipe sends than electric pulse device is little more than 10 times.
9. firing chamber according to claim 1 acoustic investigation device, is characterized in that: described upper elbow and lower elbow are right-angle elbow pipe.
10. firing chamber according to claim 1 acoustic investigation device, is characterized in that: described electric pulse device, connecting rod and rigid straight pipe are coaxial setting.
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| CN201510347545.4A CN105020051B (en) | 2015-06-19 | 2015-06-19 | A kind of combustor acoustic investigation device |
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| CN201510347545.4A CN105020051B (en) | 2015-06-19 | 2015-06-19 | A kind of combustor acoustic investigation device |
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| CN106709144A (en) * | 2016-11-22 | 2017-05-24 | 中国人民解放军装备学院 | Autocorrelation theory-based engine instability prediction and assessment method |
| CN109252982A (en) * | 2018-11-19 | 2019-01-22 | 北京理工大学 | The test method that solid propellant rocket nonlinear instability burns under overload condition |
| KR101942001B1 (en) * | 2017-08-11 | 2019-01-25 | 충남대학교산학협력단 | Frequency variable type burner |
| CN109990279A (en) * | 2019-03-14 | 2019-07-09 | 北京航空航天大学 | A kind of pulsating flow around bluff bodies burner based on acoustic excitation |
| CN112324588A (en) * | 2020-09-30 | 2021-02-05 | 中国人民解放军战略支援部队航天工程大学 | Injector capable of stably suspending fuel liquid drops in high-pressure environment |
| CN113075353A (en) * | 2021-04-01 | 2021-07-06 | 上海交通大学 | Solid propellant combustion testing device |
| CN113969849A (en) * | 2021-09-26 | 2022-01-25 | 中国人民解放军战略支援部队航天工程大学 | Single-nozzle rocket engine with modular design |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN109990279A (en) * | 2019-03-14 | 2019-07-09 | 北京航空航天大学 | A kind of pulsating flow around bluff bodies burner based on acoustic excitation |
| CN112324588A (en) * | 2020-09-30 | 2021-02-05 | 中国人民解放军战略支援部队航天工程大学 | Injector capable of stably suspending fuel liquid drops in high-pressure environment |
| CN113075353A (en) * | 2021-04-01 | 2021-07-06 | 上海交通大学 | Solid propellant combustion testing device |
| CN113969849A (en) * | 2021-09-26 | 2022-01-25 | 中国人民解放军战略支援部队航天工程大学 | Single-nozzle rocket engine with modular design |
| CN113969849B (en) * | 2021-09-26 | 2023-07-11 | 中国人民解放军战略支援部队航天工程大学 | Single-nozzle rocket engine with modularized design |
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