CN108709715B - A kind of adjustable sub--super shear layer research experiment device of incoming flow parameter wide scope - Google Patents
A kind of adjustable sub--super shear layer research experiment device of incoming flow parameter wide scope Download PDFInfo
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Abstract
The invention discloses a kind of adjustable sub--super shear layer research experiment devices of incoming flow parameter wide scope, and including the test section cavity and viewing section cavity being connected and inside is connected to, the front end of test section cavity with subsonic airflow device for being connected；Along supersonic nozzle is axially installed in test section cavity, supersonic nozzle is connected with high temperature gas flow, surpasses in it and extends through for high temperature gas flow, becomes supersonic flow；Supersonic nozzle moves towards consistent with test section cavity, and its rear end is pierced by the rear end of test section cavity；The width of supersonic nozzle is consistent with the width of test section cavity, after supersonic nozzle is installed, two independent runners up and down will be divided into test section cavity, the subsonic airflow entered is set to be divided into corresponding two-way, by two runners through passage, supersonic flow and subsonic airflow are entered in viewing section cavity by corresponding outlet, and while entrance, two kinds of air-flows carry out shear-mixeds.It can satisfy adjustable sub--super shear layer developing characteristics research of incoming flow parameter wide scope.
Description
Technical field
The invention belongs to embed rocket punching press combined engine technical field, and in particular to a kind of incoming flow parameter wide scope can
The super shear layer research experiment device in the Asia-of tune.
Background technique
The high thrust performance and punching press that embedded rocket punching press combined engine can take into account rocket engine with it are started
The high specific impulse performance of machine and by extensive concern, naturally the research of flow burning problem involved in its course of work then have weight
Want meaning.Mixed flow process between supersonic speed rocket wake flow and subsonic speed punching press air-flow for combustion chamber efficient burning and
Engine performance, which has, directly affects relationship.Therefore, very must for the compressible shear layer research of sub--super shear layer one kind
It wants.For general compressible shear-mixed flowing, the shear layer formed between rocket tail gas and punching press air-flow has speed
The features such as gradient is big, temperature gradient is big, development space is limited is spent, flow field knot stronger so as to cause shear-mixed stream compressibility
Structure is more complicated.And currently, the experimental study spininess for sub--super shear layer is terraced to relatively small velocity gradient and temperature
Spend operating condition expansion.For example, laboratory (Journal of Fluid more pneumatic than more typical Stanford university high temperature
Mechanical, 1995) compressible shear layer experimental provision is sub--super shearing of two-dimensional surface, mainly includes boost section, test
Section, expansion segment etc. are wherein made of in boost section supersonic nozzle and subsonic speed jet pipe, and centre is separated by partition；And subsonic speed
It is to enter the storage tank of certain specification by air compressor machine compression, and mention under the action of respective control valve respectively with supersonic flow
For inlet flow conditions.Velocity interval is 110~508m/s in the device experimentation, and temperature is room temperature；Later period is by improving
(doctoral thesis of Tobias Rossmann), temperature reaches as high as 700K.The domestic National University of Defense Technology it is mixed supersonic
Layer wind-tunnel (Zhao Yuxin's doctoral thesis) is vacuum pumping-type structure, is mainly used for studying the shear action between the super air-flow of super-, real
Testing temperature is room temperature, and velocity interval is 400~670m/s.Synthesis is both domestic and external the study found that Asia-super shear layer research at present
Experimental provision is directed to convective Mach Mc < 1 mostly, the case where conduct a research, Mc=(u1-u2)/(c1+c2), wherein u is air-flow
Speed, c are the local velocity of sound of air-flow, and then less for the higher corresponding experimental study of Mc state.Therefore, a kind of incoming flow ginseng
The design of adjustable sub--super shear layer research experiment device of the big gradient wide scope of number is particularly important.
Summary of the invention
Technical problem to be solved by the present invention lies in view of the above shortcomings of the prior art, providing, a kind of incoming flow parameter is wide
Adjustable sub--super shear layer research experiment device of range can satisfy adjustable sub--super shear layer hair of incoming flow parameter wide scope
Open up characteristic research.
In order to solve the above technical problems, the technical solution adopted by the present invention is that, a kind of adjustable Asia-of incoming flow parameter wide scope
Super shear layer research experiment device, including the test section cavity and viewing section cavity being connected and inside is connected to, test section cavity
Front end for being connected with subsonic airflow device；Along supersonic nozzle is axially installed in test section cavity, supersonic speed is sprayed
Pipe is connected with high temperature gas flow, interior to extend through for high temperature gas flow, becomes supersonic flow；Supersonic nozzle and test section
Moving towards for cavity is consistent, and its rear end is pierced by the rear end of test section cavity；The width of supersonic nozzle and the width of test section cavity
Spend it is consistent, install supersonic nozzle after, will be divided into test section cavity up and down two independent runners, make enter subsonic speed
Air-flow is divided into corresponding two-way, by two runners through passing through, supersonic flow and subsonic airflow by it is corresponding export into
Enter in viewing section cavity, while entrance, two kinds of air-flows carry out shear-mixeds.
It further, further include gas generator, gas generator is connected with supersonic nozzle, interior to work as difference
The ethylene of amount ratio mixes with air burning, to provide the high temperature gas flow of different temperatures.
Further, which includes being sequentially connected the supporting plate connect, combustion gas rectification section and daraf(reciprocal of farad) along air flow direction
That nozzle section；Supporting plate includes the solid wedge section of integrally connected along air flow direction and waits straight sections, waits straight sections and combustion gas rectification section
The connection of input end integral hermetic；Combustion gas rectification section and Rafael nozzle section integrally connected and it is connected, forms the cavity of perforation,
And along airflow direction, the inner mold face of Rafael nozzle section is daraf(reciprocal of farad) that structure；It is opened on combustion gas rectification section and positioned at its front end
Equipped with the external through-hole with cavity of connection.
Further, on the test section cavity and it is located at its front end, offers vertical cavity and be connected with cavity
High temperature gas flow channel, for being connected to gas generator and supersonic nozzle；In assembly, the position in high temperature gas flow channel and through-hole
Position it is corresponding.
Further, which detachably installs with supersonic nozzle, the inner wall of the front and back side of test section cavity
Upper axial direction is provided with fin, and on the outer wall of supersonic nozzle, opposite side axially offers the groove being mutually equipped with fin.
Further, the test section cavity and viewing section cavity are detachably connected, implementation are as follows: in test section cavity and
Connecting hole is opened up on viewing section cavity and positioned at junction, connecting hole is connected and fixed by fixed pin.
Further, in the combustion gas rectification section, and with through-hole opposite flank, inner sidewall along air flow direction direction be circular arc
Shape.
Further, which is installed at the axis line position of test section cavity.
Further, the wall body of the viewing section cavity uses optical glass, and optical glass passes through the cover board being arranged on
It is fixed with test section cavity, and cover board is only covered on four sides of optical glass.
The invention also discloses a kind of above-mentioned supersonic nozzle, inside communicated through for air-flow, along air flow direction
Upper includes being sequentially connected the supporting plate connect, combustion gas rectification section and Rafael nozzle section；Supporting plate includes integrally connected along air flow direction
Solid wedge section and equal straight sections, wait straight sections to connect with the input end integral hermetic of combustion gas rectification section；Combustion gas rectification section and daraf(reciprocal of farad) that
Nozzle section integrally connected and it is connected, forms the cavity of perforation, and along airflow direction, the inner mold face of Rafael nozzle section
For daraf(reciprocal of farad) that structure；On combustion gas rectification section and it is located at the through-hole that its front end offers connection outside and cavity.
A kind of adjustable sub--super shear layer research experiment device of incoming flow parameter wide scope of the present invention, which has the advantages that, to be adopted
High-temperature fuel gas is obtained with ethylene combustion heating method, and realizes the wide scope of temperature by adjusting the equivalent proportion of fuel and air
It adjusts, realizes that the wide scope of speed is adjusted by adjusting the divergence ratio of dismountable supersonic nozzle section De Laval noz(zle), and by
This obtains adjustable sub--super shear layer of incoming flow parameter wide scope；It can more really simulate in practical work process in this way
Shear-mixed effect between high-temperature fuel gas and room temperature punching press air-flow, binding test technology grasp sub--super shear layer rule of development
And incoming flow parameter arranges the enhancing mixing for proposing rationally to be applicable in practical implementation the influencing characterisitic of shear layer growth rate
It applies and lays the foundation, provide experimental data support simultaneously for sub--super this kind of turbulent flow problem of shear-mixed stream is understood in depth.Together
When, the present invention has simple, Yi Shixian advantage.
Detailed description of the invention
Fig. 1 is a kind of backsight structure of adjustable sub--super shear layer research experiment device of incoming flow parameter wide scope of the present invention
Schematic diagram.
Fig. 2 is a kind of backsight structure of adjustable sub--super shear layer research experiment device of incoming flow parameter wide scope of the present invention
The D-D sectional view of schematic diagram；
Fig. 3 is the profilograph of supersonic nozzle in the present invention；
Fig. 4 is schlieren experiment result in test section cavity；
Fig. 5 is the normalization thickness growth rate and notional result comparison diagram that schlieren experiment obtains；
Wherein: 1. test section cavitys；2. viewing section cavity；3 supersonic nozzles；3-1. supporting plate；3-2. combustion gas rectification section；3-
3. Rafael nozzle section；4. gas generator；5. observation window；6. cover board；7. high temperature gas flow channel；8. connecting hole；9. fixed pin.
Specific embodiment
A kind of adjustable sub--super shear layer research experiment device of incoming flow parameter wide scope of the present invention, as depicted in figs. 1 and 2,
Including the test section cavity 1 and viewing section cavity 2 being connected and inside is connected to, the front end of test section cavity 1 is used for and subsonic speed
Airflow apparatus is connected；Along supersonic nozzle 3 is axially installed in test section cavity 1, supersonic nozzle 3 is connected with high temperature gas flow
It is logical, it is interior to be extended through for high temperature gas flow, become supersonic flow；Supersonic nozzle 3 moves towards phase one with test section cavity 1
It causes, its rear end is pierced by the rear end of test section cavity 1；The width of supersonic nozzle 3 is consistent with the width of test section cavity 1, peace
After filling supersonic nozzle 3, two independent runners up and down will be divided into test section cavity 1, are divided into the subsonic airflow entered
Corresponding two-way, by two runners through passing through, supersonic flow enters viewing section by corresponding outlet with subsonic airflow
In cavity 2, while entrance, two kinds of air-flows carry out shear-mixeds.
Further include gas generator 4, gas generator 4 is connected with supersonic nozzle 3, in for different equivalent proportions
Ethylene mixes with air burning, to provide the high temperature gas flow of different temperatures.
As shown in figure 3, supersonic nozzle 3 includes being sequentially connected the supporting plate 3-1 connect, combustion gas rectification section 3- along air flow direction
2 and Rafael nozzle section 3-3；Supporting plate 3-1 along air flow direction include integrally connected solid wedge section and equal straight sections, wait straight sections with
The input end integral hermetic of combustion gas rectification section 3-2 connects；Combustion gas rectification section 3-2 and Rafael nozzle section 3-3 integrally connected and phase
Connection forms the cavity of perforation, and along airflow direction, the inner mold face of Rafael nozzle section 3-3 is daraf(reciprocal of farad) that structure；Combustion gas
On rectification section 3-2 and it is located at the through-hole 3-4 that its front end offers connection outside and cavity.On test section cavity 1 and it is located at it
Front end, the high temperature gas flow channel 7 for offering vertical cavity and being connected with cavity, for being connected to gas generator 4 and supersonic speed
Jet pipe 3；In assembly, the position in high temperature gas flow channel 7 is corresponding with the position of through-hole 3-4.The front end wedge structure of supporting plate 3-1
And wait straight sections that subsonic airflow can smoothly be split into two strands of air-flows up and down.
For change Rafael nozzle section 3-3 different divergence ratios, reach speed wide scope variation, test section cavity 1 with
Supersonic nozzle 3 is detachably installed, and is axially provided with fin on the inner wall of the front and back side of test section cavity 1, supersonic nozzle 3
On outer wall, opposite side axially offers the groove being mutually equipped with fin.
In the present invention, test section cavity 1 and viewing section cavity 2 are detachably connected, implementation are as follows: in test section cavity 1
Connecting hole 8 is opened up on viewing section cavity 2 and positioned at junction, connecting hole 8 is connected and fixed by fixed pin 9.Combustion gas rectification section
In 3-2, and with the opposite flank through-hole 3-4, inner sidewall along air flow direction direction be arc-shaped.Supersonic nozzle 3 is installed on test
At the axis line position of section cavity 1.The wall body of viewing section cavity 2 uses optical glass, and optical glass, which passes through, to be arranged on
Cover board 6 and test section cavity 1 are fixed, and cover board 6 is only covered on four sides of optical glass, i.e. four sides turn on window, not by
The glass of covering forms observation window 5.
The invention also discloses a kind of above-mentioned supersonic nozzle, inside communicated through for air-flow, along air flow direction
Upper includes being sequentially connected the supporting plate 3-1 connect, combustion gas rectification section 3-2 and Rafael nozzle section 3-3；Supporting plate 3-1 is along air flow direction packet
The solid wedge section and grade straight sections for including integrally connected, wait straight sections and the input end integral hermetic of combustion gas rectification section 3-2 to connect；Combustion gas
Rectification section 3-2 and Rafael nozzle section 3-3 integrally connected and it is connected, forms the cavity of perforation, and along airflow direction,
The inner mold face of Rafael nozzle section 3-3 is daraf(reciprocal of farad) that structure；It is outer that connection is offered on combustion gas rectification section 3-3 and positioned at its front end
The through-hole 3-4 in portion and cavity.In combustion gas rectification section 3-2, and with the opposite flank through-hole 3-4, inner sidewall is along air flow direction direction
For arc-shaped.Reduce air-flow pitot loss, while playing certain thickening protective effect to combustion gas rectification section, avoids high-temperature fuel gas
Stream burns out structure；Gas generator 4 is to be fixedly connected by screw and test section cavity 1, and use graphite-seal ring
It is sealed；Guarantee that its high temperature gas flow channel 7 is corresponding with the outlet of gas generator 4.Supersonic nozzle 3 is then directly inserted into examination
It tests in section cavity 1, waits the side of straight sections also to open up threaded hole, and be connected to the circular hole of 1 same position of test section cavity, pass through spiral shell
Nail positions supersonic nozzle 3.The head of gas generator 4 is connect with ethylene supply system and air supply system respectively,
Middle oxygen content is 30%, and burning generates high-temperature fuel gas under the action of high-energy igniter.Low-speed flow supply system then passes through spiral shell
Bolt is connect with test section cavity 1, and is sealed with O-ring, to provide subsonic airflow.Subsonic airflow is then by a series of high
Air bottle is in parallel, obtains under the adjusting control action of pressure reducer and flowmeter, and air-flow is gas at normal temperature, and velocity interval is 0~
300m/s。
High-temperature fuel gas is obtained using ethylene combustion heating method in the present invention, and by adjusting the equivalent proportion of ethylene and air
To realize that the wide scope of temperature is adjusted, realize that the wide scope of speed is adjusted by adjusting dismountable 3 divergence ratio of supersonic nozzle,
And thus to obtain adjustable sub--super shear layer of incoming flow parameter wide scope；Real work can be more really simulated in this way
Shear-mixed effect between the combustion gas of journey high temperature and room temperature punching press air-flow, binding test technology grasp sub--super shear layer development
Rule and incoming flow parameter mix the enhancing for proposing rationally to be applicable in practical implementation the influencing characterisitic of shear layer growth rate
Conjunction measure lays the foundation, and provides experimental data branch simultaneously for sub--super this kind of turbulent flow problem of shear-mixed stream is understood in depth
Support.
The chemical reaction formula of ethylene and oxygen in gas generator 4 are as follows:
Warm calculation procedure is fired by CEA and knows that ethylene fuel gas temperature under the conditions of equivalent proportion can reach 2795K, can be simulated true
Fuel gas temperature under the conditions of positive activity, the experiment condition being capable of providing under the conditions of convective Mach Mc > 1；In addition, in order to mould
Intend the super shear layer developing characteristics in Asia-under the conditions of different convective Mach, can be realized by adjusting the equivalent proportion of ethylene and air
Control to fuel gas temperature；Simultaneously can by adjusting Rafael nozzle section 3-3 divergence ratio to realize supersonic flow speed
Wide scope variation, and then realize the super shear layer experimental study in Asia under the conditions of high convective Mach Mc.
In order to realize before the research to sub--super shear layer developing characteristics, experiment start firstly the need of this test of determination
State, according to the convective Mach Mc value of planning experiment, determine subsonic airflow and supersonic flow incoming flow pressure value,
Total temperature and Mach number or speed.Then the supersonic nozzle 3 of corresponding design Mach number is installed in test section cavity 1, and
It is fixed with positioning pin；Then observation window is installed in place, and is fixed using screw.In addition, according to acquisition is calculated
Supersonic flow total temperature fires warm calculation procedure in conjunction with CEA, adjusts to the flow of ethylene control system and air supply system
Section reaches expected combustion temperature；Meanwhile low-speed flow supply system pressure is adjusted, control subsonic airflow Mach number and pressure and design
State consistency.Finally test macro is installed in place, in this test using schlieren system to sub- super shear layer developing characteristics into
Row research.So far, preparation is completely ready before testing.
It is first turned on low-speed flow supply system in experimentation, guarantees that subsonic airflow is introduced into test section cavity 1；3s
Ethylene supply system and air supply system are opened afterwards, supply ethylene respectively and air enters in gas generator 4, are ethylene
Full combustion provides mixed uniformly environment, opens schlieren system at the same time and is observed to by observation window 5；It is opened after 2s again
Dynamic high-energy igniter, lights ethylene, and the full combustion in gas generator 4, the high-temperature fuel gas of generation is in supersonic nozzle 3
Supersonic flows are realized under acceleration and are entered in test section cavity 1, and shear-mixed effect occurs with subsonic airflow.After 8s
High-energy igniter is closed, ethylene supply system and air supply system is turned off after 3s, simultaneously closes off schelieren system, finally
Turn off low-speed flow supply system.So far, this experiment has been fully completed.
Table 1 is shown with the experiment work of developing characteristics research of the experimental provision to shear layer sub--super under normal temperature condition
Condition and result treatment.Wherein, Dc is compressible shear layer thickness growth rate；Di be under the conditions of identical speed ratio and density ratio not
The ratio between compressible shear layer thickness growth rate, Dc/Di are to normalize thickness growth rate to obtain what the experimental provision obtained by table 1
Sub--super shear layer thickness growth rate equivalent depth growth rate and notional result are almost the same, and error is only 2%.
Sub--super shear layer inlet flow conditions of table 1 and result
Fig. 4 is that table 1 is sub-, the schlieren experiment under supersonic flow inlet flow conditions is as a result, wherein upper and lower two-way is subsonic speed gas
Stream, center stream are supersonic flow, it can be seen that in outlet port, upper layer subsonic airflow and supersonic flow and lower layer surpass
Apparent shear mixing layers are formed between subsonic airflow and subsonic airflow, boundary is more apparent, can carry out sub--super shear layer along stream
Research to rising characteristic；Furthermore there is dilatational wave in outlet in center supersonic flow, downward by the reflex of shear layer
Trip development, forms a series of wave system structures, by Fig. 4 it can be found that non-homogeneous increasing is presented in shear layer thickness under wave system structure function
Research can be developed in details in long characteristic, the feature.
Fig. 5 is shown under this experimental state by between the schlieren shear layer normalization thickness growth rate obtained and notional result
Comparison, discovery error is smaller, and error is 2% as shown in Table 1, meets requirement of experiment.Notional result is referring to bibliography
Turbulent Free Shear Layer Mixing and Combustion,P.E.Dimotakis,AIAA,1991,
Chapter 5.Thereby determine that experimental provision can satisfy adjustable sub--super shear layer research work of incoming flow parameter wide scope.
Claims (10)
1. a kind of adjustable sub--super shear layer research experiment device of incoming flow parameter wide scope, which is characterized in that including being connected and
The front end of the test section cavity (1) and viewing section cavity (2) of inside connection, the test section cavity (1) is used for and subsonic speed gas
Stream device is connected；Along being axially installed with supersonic nozzle (3) in the test section cavity (1), the supersonic nozzle (3) with
High temperature gas flow is connected, interior to extend through for high temperature gas flow, becomes supersonic flow；The width of supersonic nozzle (3) with
The width of test section cavity (1) is consistent, after installation supersonic nozzle (3), will be divided into upper and lower two solely in test section cavity (1)
Vertical runner makes the subsonic airflow entered be divided into corresponding two-way, by two runners through passage, supersonic flow and Asia
Subsonic airflow is entered in viewing section cavity (2) by corresponding outlet, and while entrance, two kinds of air-flows carry out shear-mixeds.
2. a kind of adjustable sub--super shear layer research experiment device of incoming flow parameter wide scope according to claim 1, special
Sign is, further includes gas generator (4), and the gas generator (4) is connected with supersonic nozzle (3), interior for not
Ethylene with equivalent proportion mixes with air burning, to provide the high temperature gas flow of different temperatures.
3. a kind of adjustable sub--super shear layer research experiment device of incoming flow parameter wide scope according to claim 1 or 2,
It is characterized in that, the supersonic nozzle (3) includes being sequentially connected supporting plate (3-1), the combustion gas rectification section connect along air flow direction
(3-2) and Rafael nozzle section (3-3)；The supporting plate (3-1) includes the solid wedge section of integrally connected along air flow direction and waits
Straight section waits straight sections and the input end integral hermetic of combustion gas rectification section (3-2) to connect；The combustion gas rectification section (3-2) and daraf(reciprocal of farad) that
Nozzle section (3-3) integrally connected and it is connected, forms the cavity of perforation, and along airflow direction, the Rafael nozzle section
The inner mold face of (3-3) is daraf(reciprocal of farad) that structure；On the combustion gas rectification section (3-2) and be located at its front end offer connection it is external with
The through-hole (3-4) of cavity.
4. a kind of adjustable sub--super shear layer research experiment device of incoming flow parameter wide scope according to claim 3, special
Sign is, on the test section cavity (1) and is located at its front end, the High Temperature Gas for offering vertical cavity and being connected with cavity
Circulation road (7), for being connected to gas generator (4) and supersonic nozzle (3)；In assembly, the position of high temperature gas flow channel (7)
It is corresponding with the position of through-hole (3-4).
5. a kind of adjustable sub--super shear layer research experiment device of incoming flow parameter wide scope according to claim 4, special
Sign is, in the combustion gas rectification section (3-2), and with the opposite flank through-hole (3-4), inner sidewall is circular arc along air flow direction direction
Shape.
6. a kind of adjustable sub--super shear layer research experiment device of incoming flow parameter wide scope according to claim 5, special
Sign is that the test section cavity (1) and supersonic nozzle (3) are detachably installed, the front and back side of the test section cavity (1)
Axially it is provided with fin on inner wall, on the outer wall of the supersonic nozzle (3), opposite side is axially offered mutually to be equipped with fin
Groove.
7. a kind of adjustable sub--super shear layer research experiment device of incoming flow parameter wide scope according to claim 6, special
Sign is that the test section cavity (1) and viewing section cavity (2) are detachably connected, implementation are as follows: in test section cavity (1)
It is opened up connecting hole (8) on viewing section cavity (2) and positioned at junction, connecting hole (8) is connected and fixed by fixed pin (9).
8. a kind of adjustable sub--super shear layer research experiment device of incoming flow parameter wide scope according to claim 7, special
Sign is that the supersonic nozzle (3) is installed at the axis line position of test section cavity (1).
9. a kind of adjustable sub--super shear layer research of incoming flow parameter wide scope according to any one of claim 5-8 is real
Experiment device, which is characterized in that the wall body of the viewing section cavity (2) uses optical glass, and optical glass is by being arranged on
Cover board (6) and test section cavity (1) it is fixed, and cover board (6) is only covered on four sides of optical glass, uncovered glass
Glass forms observation window (5).
10. a kind of supersonic nozzle, which is characterized in that communicated through inside it for air-flow, include successively along air flow direction
Supporting plate (3-1), combustion gas rectification section (3-2) and the Rafael nozzle section (3-3) being connected；The supporting plate (3-1) is along air flow direction
Solid wedge section and equal straight sections including integrally connected, wait straight sections and the input end integral hermetic of combustion gas rectification section (3-2) to connect；
The combustion gas rectification section (3-2) and Rafael nozzle section (3-3) integrally connected and it is connected, forms the cavity of perforation, and on edge
On airflow direction, the inner mold face of the Rafael nozzle section (3-3) is daraf(reciprocal of farad) that structure；On the combustion gas rectification section (3-2),
And it is located at its front end and offers the external through-hole (3-4) with cavity of connection.
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