CN104791134A - Flow field visualization device with replaceable secondary flow unlike-impinging nozzle - Google Patents
Flow field visualization device with replaceable secondary flow unlike-impinging nozzle Download PDFInfo
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- CN104791134A CN104791134A CN201510232719.2A CN201510232719A CN104791134A CN 104791134 A CN104791134 A CN 104791134A CN 201510232719 A CN201510232719 A CN 201510232719A CN 104791134 A CN104791134 A CN 104791134A
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Abstract
The invention relates to a flow field visualization device with a replaceable secondary flow unlike-impinging nozzle, and belongs to the field of fluid jet engines. The device comprises a nozzle seal gasket, a nozzle press plate, a secondary jet flow injecting device, an unlike-impinging jet nozzle, quartz glass, a visual window, a spray pipe and the like. According to the flow field visualization device with the replaceable secondary flow unlike-impinging nozzle, the atomization condition, inner flow field distribution and flow field speed distribution can be measured through the visual window, the actual effective throat area and flow field distribution after inducing shock waves are formed can be observed through the visual window, and the specific changing process of thrust adjusting can be seen visually. In the process of measuring the flow field distribution and the atomization condition under different schemes and the changing process of thrust adjusting under the various schemes, it is unnecessary to replace the whole spray pipe device, and the processes can be achieved just by replacing jet nozzles with different secondary flow unlike-impinging angles or placing a plug in a corresponding liquid collecting cavity.
Description
Technical field
The present invention relates to the flow field visual device that a kind of replaceable Secondary Flow hits nozzle mutually, belong to the engine art of Fluid injection.
Background technique
A secondary fluid sprays and refers to that secondary jet and main flow interact by injection secondary jet in the main flow of engine jet pipe throat or nozzle divergence cone, changes main flow flow condition, thus the size and Orientation of change motor power.Thrust is regulated to be the research field of Thrust of Solid Rocket Motor regulation technology by changing nozzle throat area.
Number of patent application 201510017390.8, a kind of a secondary fluid jet thrust controlling device of replaceable jet pipe, the object of this invention achieves the size control of thrust and the direction adjustment of thrust.But there is following shortcoming in this device: 1 is merely able to the size and Orientation realizing regulating thrust, can not see that thrust regulates the detailed process of change intuitively, Flow Field Distribution when Laval nozzle throat or extending section place Secondary Flow and main flow interact can not be measured, velocity distribution and atomizing effect; 2 will change whole bulky jet pipe when carrying out kinds of schemes and measuring; 3 a secondary fluid spray regimes are horizontal correlation jet under normal circumstances and reversed injection.
Summary of the invention
The object of the invention is to solve above-mentioned shortcoming, a kind of replaceable Secondary Flow is provided to hit the flow field visual device of nozzle mutually, this device measures atomization situation, flow field distribution and flow field velocity distribution by visual window, intuitively can arrive the detailed process that thrust regulates change.
The object of the invention is to be achieved through the following technical solutions.
Replaceable Secondary Flow hits a flow field visual device for nozzle mutually, comprising: sealed nozzle pad, nozzle place pressing plate, secondary jet injection device, hit jet nozzles, silica glass, visualization window and jet pipe mutually;
Hit jet nozzles mutually to comprise: spray liquid collecting cavity, slotted countersunk flat head screw, sealing O type circle, blocking;
Hitting jet nozzles is mutually the cuboids of both sides with boss; Two identical injection liquid collecting cavities are offered from bottom surface symmetry; Spray liquid collecting cavity for placing blocking; Spray liquid collecting cavity bottom surface and offer angled through hole; Blocking outside cover has sealing O type circle, and blocking center has tapped hole, for being fixedly connected with slotted countersunk flat head screw; The end face hitting jet nozzles mutually act as the throat of Laval nozzle, partial convergence section and part extending section;
Hitting jet nozzles is mutually placed in jet pipe; Through hole is offered, for liquid communication in the middle of sealed nozzle pad and nozzle place pressing plate; Sealed nozzle pad is fixedly connected with jet pipe by screw with nozzle place pressing plate, is fixed in jet pipe by hitting jet nozzles mutually; Nozzle place pressing plate is fixedly connected with secondary jet injection device; On two faces adjacent with secondary jet injection device, symmetry is placed silica glass and is formed visualization window;
Described number of openings is at least 2.
Working procedure: during engine work, mainstream gas by motor Laval nozzle converging portion, expands after nozzle throat and nozzle divergence cone and accelerates, produce thrust; Meanwhile secondary jet is by the symmetrical injecting jet liquid collecting cavity of secondary jet injection device, secondary jet forms the liquid stream of stable pressure spraying liquid collecting cavity, inject nozzle throat or jet pipe expanding section more uniformly, thus acutely extrude with high pressure mainstream gas or chemical reaction occurs and produce and be atomized flow field, measure atomization situation, flow field distribution and flow field velocity distribution by visualization window, now also can see the change procedure that thrust regulates intuitively.If secondary jet sprays in throat's symmetry, play the effect regulating throat area, the effective throat opening area in gas-liquid impingement situation can be observed by visualization window, that can understand Secondary Flow intuitively grips larynx ability, thus intuitively can arrive the change procedure of thrust adjustment; If by blocking single being placed on, nozzle divergence cone Secondary Flow is asymmetrical sprays into, then observe the Flow Field Distribution after forming induction shock wave by visualization window, thus intuitively arrive the process of thrust direction adjustment.
When needing to carry out the flow field survey under multi-scheme according to real work, jet nozzles can be hit mutually by the position or replacing controlling blocking and change ejection schemes, the Renewal process hitting jet nozzles and blocking is mutually, mounting type is: take out to change different hit hitting jet nozzles mutually or choosing the ejection schemes that will implement of angular arrangements mutually hitting jet nozzles mutually, then blocking is put into and spray liquid collecting cavity accordingly, carry out throat or extending section injection Secondary Flow again, now seal O type circle and place blocking side, serve good seal action, blocking screwed hole of centre is fixedly connected with slotted countersunk flat head screw, then sealed nozzle pad and nozzle place pressing plate are installed, finally utilize screw to tighten fixing by itself and whole Effuser device.
Dismounting mode: by unloading screw, can take out secondary jet injection device and nozzle place pressing plate, sealed nozzle pad successively, also can take out and hit jet nozzles mutually; Then slotted countersunk flat head screw is screwed out a part outward, then blocking can be taken out from liquid collecting cavity with pliers.
Beneficial effect
1, a kind of replaceable Secondary Flow of the present invention hits the flow field visual device of nozzle mutually, measures atomization situation, flow field distribution and flow field velocity distribution by visualization window; Also can observe actual effective throat opening area by visualization window and form the Flow Field Distribution after inducing shock wave, can see that thrust regulates the detailed process of change intuitively.
2, a kind of replaceable Secondary Flow of the present invention hits the flow field visual device of nozzle mutually, be only suitable for the measurement in gas-liquid impingement flow field, when measuring the change procedure that the Flow Field Distribution under different schemes regulates with thrust under atomization situation and kinds of schemes, do not need to change whole Effuser device, as long as change different secondary stream to hit hitting jet nozzles mutually or blocking being placed in corresponding liquid collecting cavity of angle mutually.
3, a kind of replaceable Secondary Flow of the present invention hits the flow field visual device of nozzle mutually, wherein, secondary jet is when throat or extending section and main flow occur to interact, the incidence of secondary jet is not horizontal correlation and reversed injection, but the collision jet that the multiple through holes adopted are angled.
4, a kind of replaceable Secondary Flow of the present invention hits the flow field visual device of nozzle mutually, compare with the horizontal correlation jet of Secondary Flow and reversed injection, under the jet of same traffic, Secondary Flow is mapped to when throat or extending section and mainstream gas interact can produces larger thrust through hitting jet nozzles jet mutually.
Accompanying drawing explanation
Fig. 1 is the half sectional view that a kind of replaceable Secondary Flow of the present invention hits the symmetrical spray regime of flow field visual device employing nozzle throat of nozzle mutually.
Wherein: 1-sealed nozzle pad, 2-nozzle place pressing plate, 3-spray liquid collecting cavity, 4-secondary jet injection device, 5-slotted countersunk flat head screw, 6-sealing O type circle, 7-blocking, 8-hit jet nozzles, 9-silica glass, 10-visualization window, 11-jet pipe mutually;
Embodiment
Below in conjunction with drawings and Examples, the present invention is described further.
Embodiment 1
Replaceable Secondary Flow hits a flow field visual device for nozzle mutually, comprising: sealed nozzle pad 1, nozzle place pressing plate 2, secondary jet injection device 4, hit jet nozzles 8, silica glass 9, visualization window 10 and jet pipe 11 mutually;
Hit jet nozzles 8 mutually to comprise: spray liquid collecting cavity 3, slotted countersunk flat head screw 5, sealing O type circle 6, blocking 7;
Hitting jet nozzles 8 is mutually the cuboids of both sides with boss; Two identical injection liquid collecting cavities 3 are offered from bottom surface symmetry; Spraying liquid collecting cavity 3 for placing blocking 7, paired for blocking 7 being placed on being hit mutually injection liquid collecting cavity 3 corresponding to jet nozzles 8 extending section, thus ensure that Secondary Flow can only be sprayed by the injection liquid collecting cavity 3 that place of throat is corresponding; Spray liquid collecting cavity 3 bottom surface and offer angled through hole, number of openings is 3, and 3 through holes are that axisymmetric is arranged with intermediate hole, and hitting total angle is mutually 60 °; Outside blocking 7, cover has sealing O type circle 6, and 7 centers that block have tapped hole, for being fixedly connected with slotted countersunk flat head screw 5; The end face hitting jet nozzles 8 mutually act as the throat of Laval nozzle, partial convergence section and part extending section;
Hitting jet nozzles 8 is mutually placed in jet pipe 11; Through hole is offered in the middle of sealed nozzle pad 1 and nozzle place pressing plate 2; Sealed nozzle pad 1 is fixedly connected with jet pipe 11 by screw with nozzle place pressing plate 2, is fixed in jet pipe 11 by hitting jet nozzles 8 mutually; Nozzle place pressing plate 2 is fixedly connected with secondary jet injection device 4; On two faces adjacent with secondary jet injection device 4, symmetry is placed silica glass 9 and is formed visualization window 10;
Described sealed nozzle pad 1 is arranged symmetrically with, compress and hit jet nozzles 8 mutually, serve good seal action, liquid collecting cavity 3 is sprayed by pushing down, prevent injection liquid collecting cavity 3 intravenous extravasation or air from entering on the one hand and spray liquid collecting cavity 3, oppositely leaking in the gap on the other hand preventing again the mainstream gas at throat or extending section place and liquid to flow through to hit mutually jet nozzles 8 to coordinate with jet pipe 11, successfully ensure that the sealing of device; The intermediate throughholes of sealed nozzle pad 1 is also as the passageway of Secondary Flow simultaneously, Secondary Flow triumph is flowed into and sprays liquid collecting cavity 3.
Described nozzle place pressing plate 2 is arranged symmetrically with, and effect is to compress sealed nozzle pad 1, allows the sealed nozzle pad 1 compressed can have good seal action; Nozzle place pressing plate 2 intermediate throughholes also serves the passageway as second liquid flow, and the passageway through compressing sealed nozzle pad 1 flows into sprays liquid collecting cavity 3.
Described injection liquid collecting cavity 3 is by hitting the deep hole cavity that jet nozzles 8 bottom surface is formed mutually, in cavity, the liquid stream stablizing pressure is formed for making secondary jet, make to inject nozzle throat or extending section in throat or extending section secondary jet with the form of hitting mutually, thus ensure that throat or extending section have stable jet pressure, then there is strong interaction with main flow.
Described secondary jet injection device 4, for introducing secondary jet to injection liquid collecting cavity 3, has gone through sealed nozzle pad 1, passageway, nozzle place pressing plate 2 liang place; Secondary jet injection device 4 symmetry is connected to the both sides of Effuser device, for offsetting the impact that secondary jet is produced motor power by secondary jet injection device 4 injecting jet liquid collecting cavity 3;
Described slotted countersunk flat head screw 5 blocking 7 is taken out or put into spray liquid collecting cavity 3, thus realize the observation of multiple ejection schemes Fluid field.
Described sealing O type circle 6 plays seal action when carrying out the observation in multiple flow field with blocking 7, prevents Secondary Flow from the side permeate of blocking 7 to injection liquid collecting cavity 3.
Described blocking 7 is in order to Control release scheme, single or paired for blocking 7 being placed on can be hit mutually the injection liquid collecting cavity 3 of jet nozzles 8 throat or extending section, realize the observation in multiple flow field, its mode can have: secondary jet spray regime is nozzle throat symmetric mode, or the symmetrical spray regime of nozzle divergence cone, or the spray regime of nozzle throat and nozzle divergence cone combination.
Described jet nozzles 8 effect of hitting mutually by injection liquid collecting cavity 3, second liquid flow is injected throat or extending section and mainstream gas to form violent shock, is atomized into very little drop.Hit the both sides that jet nozzles 8 symmetry is placed on jet pipe 11 device mutually, so that the impact that counteracting secondary jet is produced motor power by secondary jet injection device 4 injecting jet liquid collecting cavity;
Described visualization window 10 refers to the silica glass 9 after by sealing, adds screwing and is fixed in jet pipe 11, then measures atomization situation, flow field distribution and flow field velocity distribution by visualization window 10.Described silica glass 9 transmittance is high, provides visual condition.
Described jet pipe 11 changes on existing nozzle structure, and being designed with can with the passage hitting jet nozzles 8 and silica glass 9 mutually and match; Described jet pipe main flow circulation inner mold face comprises jet area contraction section, nozzle throat, nozzle divergence cone; Its throat's section not on the jet pipe 11 of itself, and is positioned at the end face hitting jet nozzles 8 mutually; Also some is positioned at the end face hitting jet nozzles 8 mutually for extending section and converging portion.
Working procedure:
During engine work, mainstream gas by motor Laval nozzle converging portion, expands after nozzle throat and nozzle divergence cone and accelerates, produce thrust; Meanwhile secondary jet is injected into the injection liquid collecting cavity 3 at place of throat by secondary jet injection device 4 symmetry, secondary jet stablizes the liquid stream of pressure spraying liquid collecting cavity 3 formation, inject nozzle throat uniformly again, thus acutely extrude with high pressure mainstream gas or chemical reaction occurs and produce and be atomized flow field, measure atomization situation, flow field distribution and flow field velocity distribution by visualization window 10; Secondary jet sprays in throat's symmetry, plays the effect regulating throat area, the effective throat opening area in gas-liquid impingement situation now can be observed by visualization window 10, that can understand Secondary Flow intuitively grips larynx ability, thus intuitively can arrive the change procedure of thrust adjustment.
When flow field survey under needing to study the different spray regime of Secondary Flow or difference and hitting angular arrangements mutually, ejection schemes can be changed by the position of control blocking 7 in liquid collecting cavity or the different jet nozzles 8 that hits mutually hitting angle mutually of replacing, the Renewal process hitting jet nozzles 8 and blocking 7 is mutually, mounting type is: take out to change different hit hitting jet nozzles 8 mutually or choosing the ejection schemes that will implement of angular arrangements mutually hitting jet nozzles 8 mutually, then blocking 7 is put into and spray liquid collecting cavity accordingly, carry out throat or extending section injection Secondary Flow again, now seal O type circle 6 and place blocking 7 side, serve good seal action, block 7 screwed hole of centre to be fixedly connected with slotted countersunk flat head screw 5, then sealed nozzle pad 1 and nozzle place pressing plate 2 are installed, finally utilize screw to tighten fixing by itself and whole jet pipe 11 device.
Dismounting mode: by unloading screw, can take out secondary jet injection device 4 and nozzle place pressing plate 2, sealed nozzle pad 1 successively, also can take out and hit jet nozzles 8 mutually; Then slotted countersunk flat head screw 5 is screwed out a part outward, then with pliers, blocking 7 is taken out from injection liquid collecting cavity 3.
Above embodiment is only a specific embodiment of the present invention, is not intended to limit protection scope of the present invention.Within the spirit and principles in the present invention all, any amendment done, equivalent replacement, improvement etc., all should be included within protection scope of the present invention.
Claims (3)
1. replaceable Secondary Flow hits a flow field visual device for nozzle mutually, it is characterized in that: comprising: sealed nozzle pad (1), nozzle place pressing plate (2), secondary jet injection device (4), hit jet nozzles (8), silica glass (9), visualization window (10) and jet pipe (11) mutually;
Hit jet nozzles (8) mutually to comprise: spray liquid collecting cavity (3), slotted countersunk flat head screw (5), sealing O type circle (6), blocking (7);
Hit jet nozzles (8) mutually for both sides are with the cuboid of boss; Two identical injection liquid collecting cavities (3) are offered from bottom surface symmetry; Spray liquid collecting cavity (3) for placing blocking (7); Spray liquid collecting cavity (3) bottom surface and offer angled through hole; Blocking (7) outside cover has sealing O type circle (6), and blocking (7) center has tapped hole, for being fixedly connected with slotted countersunk flat head screw (5); The end face hitting jet nozzles (8) mutually act as the throat of Laval nozzle, partial convergence section and part extending section;
Hitting jet nozzles (8) is mutually placed in jet pipe (11); Through hole is offered, for liquid communication in the middle of sealed nozzle pad (1) and nozzle place pressing plate (2); Sealed nozzle pad (1) is fixedly connected with jet pipe (11) by screw with nozzle place pressing plate (2), is fixed in jet pipe (11) by hitting jet nozzles (8) mutually; Nozzle place pressing plate (2) is fixedly connected with secondary jet injection device (4); On two faces adjacent with secondary jet injection device (4), symmetry is placed silica glass (9) and is formed visualization window (10) afterwards.
2. a kind of replaceable Secondary Flow as claimed in claim 1 hits the flow field visual device of nozzle mutually, it is characterized in that: described number of openings is at least 2.
3. a kind of replaceable Secondary Flow as claimed in claim 1 hits the flow field visual device of nozzle mutually, it is characterized in that: working procedure: during engine work, mainstream gas by motor Laval nozzle converging portion, expands after nozzle throat and nozzle divergence cone and accelerates, produce thrust; Meanwhile secondary jet is by the symmetrical injecting jet liquid collecting cavity (3) of secondary jet injection device (4), secondary jet stablizes the liquid stream of pressure spraying liquid collecting cavity (3) formation, inject nozzle throat or jet pipe expanding section more uniformly, thus acutely extrude with high pressure mainstream gas or chemical reaction occurs and produce and be atomized flow field, measure atomization situation, flow field distribution and flow field velocity distribution by visualization window (10), now also can see the change procedure that thrust regulates intuitively; If secondary jet sprays in throat's symmetry, play the effect regulating throat area, can pass through visualization window (10) observe gas-liquid impingement situation under effective throat opening area, that can understand Secondary Flow intuitively grips larynx ability, thus intuitively can arrive the change procedure of thrust adjustment; Spray into if will block (7) single being placed on nozzle divergence cone Secondary Flow is asymmetrical, then observe the Flow Field Distribution after forming induction shock wave by visualization window (10), thus intuitively arrive the process of thrust direction adjustment;
When needing to carry out the flow field survey under multi-scheme according to real work, jet nozzles (8) can be hit mutually by the position or replacing controlling blocking (7) and change ejection schemes, the Renewal process hitting jet nozzles (8) and blocking (7) is mutually, mounting type is: take out to change different hit hitting jet nozzles (8) mutually or choosing the ejection schemes that will implement of angular arrangements mutually hitting jet nozzles (8) mutually, then blocking (7) is put into and spray liquid collecting cavity accordingly, carry out throat or extending section injection Secondary Flow again, now seal O type circle (6) and place blocking (7) side, serve good seal action, blocking (7) screwed hole of centre is fixedly connected with slotted countersunk flat head screw (5), then sealed nozzle pad (1) and nozzle place pressing plate (2) are installed, finally utilize screw to tighten fixing by itself and whole jet pipe (11) device.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201510232719.2A CN104791134B (en) | 2015-05-08 | 2015-05-08 | A kind of replaceable Secondary Flow hits the flow field visual device of nozzle mutually |
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| CN201510232719.2A CN104791134B (en) | 2015-05-08 | 2015-05-08 | A kind of replaceable Secondary Flow hits the flow field visual device of nozzle mutually |
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| CN104791134B CN104791134B (en) | 2016-07-06 |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN105952552A (en) * | 2016-04-29 | 2016-09-21 | 北京航空航天大学 | Rectangular transparent combustion chamber for optical diagnosis of small rocket engine |
| CN106053015A (en) * | 2016-06-01 | 2016-10-26 | 北京理工大学 | Detachable cryogenic liquid cavitation flow observational test section |
| CN106640418A (en) * | 2016-12-21 | 2017-05-10 | 中国燃气涡轮研究院 | Variable Mach number rotating mechanism based on semicircular bearings |
| CN107246969A (en) * | 2017-06-05 | 2017-10-13 | 哈尔滨工程大学 | Simulation constant volume bullet internal spraying hits wall and its induces the experimental provision of shock wave transmittance process |
| CN107462501A (en) * | 2017-08-14 | 2017-12-12 | 北京理工大学 | Online grain diameter measurement and synchronous collection system for micro-nano particle in multiphase flow |
| CN107655694A (en) * | 2017-08-24 | 2018-02-02 | 南京理工大学 | A kind of supersonic nozzle jet blends experimental provision |
| CN108613749A (en) * | 2018-04-24 | 2018-10-02 | 中国核动力研究设计院 | A kind of visualization device tilting cambered surface flow-passage-changeable |
| US10369582B2 (en) | 2015-04-30 | 2019-08-06 | Emissol Llc | System and method for spray visualization |
| CN110411706A (en) * | 2019-07-01 | 2019-11-05 | 天津大学 | Device for optical measurement calibration in wall flow field close at the top of combustion chambers of internal combustion engines |
| CN114778757A (en) * | 2022-04-01 | 2022-07-22 | 北京理工大学 | Cross-shaped visual vibration experiment engine |
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| US10369582B2 (en) | 2015-04-30 | 2019-08-06 | Emissol Llc | System and method for spray visualization |
| CN105952552B (en) * | 2016-04-29 | 2017-10-10 | 北京航空航天大学 | A kind of gular transparent combustion chamber of small rocket motor optical diagnostics |
| CN105952552A (en) * | 2016-04-29 | 2016-09-21 | 北京航空航天大学 | Rectangular transparent combustion chamber for optical diagnosis of small rocket engine |
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| CN106640418A (en) * | 2016-12-21 | 2017-05-10 | 中国燃气涡轮研究院 | Variable Mach number rotating mechanism based on semicircular bearings |
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| CN107462501B (en) * | 2017-08-14 | 2019-07-26 | 北京理工大学 | Online grain diameter measurement and synchronous collection system for micro-nano particle in multiphase flow |
| CN107462501A (en) * | 2017-08-14 | 2017-12-12 | 北京理工大学 | Online grain diameter measurement and synchronous collection system for micro-nano particle in multiphase flow |
| CN107655694A (en) * | 2017-08-24 | 2018-02-02 | 南京理工大学 | A kind of supersonic nozzle jet blends experimental provision |
| CN108613749A (en) * | 2018-04-24 | 2018-10-02 | 中国核动力研究设计院 | A kind of visualization device tilting cambered surface flow-passage-changeable |
| CN110411706A (en) * | 2019-07-01 | 2019-11-05 | 天津大学 | Device for optical measurement calibration in wall flow field close at the top of combustion chambers of internal combustion engines |
| CN110411706B (en) * | 2019-07-01 | 2020-09-01 | 天津大学 | Device for optical measurement and calibration of near-wall flow field at top of combustion chamber of internal combustion engine |
| CN114778757A (en) * | 2022-04-01 | 2022-07-22 | 北京理工大学 | Cross-shaped visual vibration experiment engine |
| CN114778757B (en) * | 2022-04-01 | 2024-04-05 | 北京理工大学 | Cross visual vibration experiment engine |
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