CN103149009B - Supersonic speed distance piece flow tunnel testing device - Google Patents
Supersonic speed distance piece flow tunnel testing device Download PDFInfo
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- CN103149009B CN103149009B CN201310057011.9A CN201310057011A CN103149009B CN 103149009 B CN103149009 B CN 103149009B CN 201310057011 A CN201310057011 A CN 201310057011A CN 103149009 B CN103149009 B CN 103149009B
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Abstract
The invention discloses a kind of supersonic speed distance piece flow tunnel testing device, this device comprises: for collecting the gas collector of gas, the outlet of gas collector connects and is used for the stable section that stabilizing gas gatherer exports the air velocity distribution of gas, the outlet of stable section is connected with the supersonic nozzle section for accelerating air-flow velocity, the outlet of supersonic nozzle section is connected with the experimental section of the distance piece configuration for analog isolation section, and the diffuser of the air-flow in the experimental section of distance piece configuration through being connected with the outlet of the experimental section of distance piece configuration is discharged.The present invention sets gradually gas collector, stable section and supersonic nozzle section by the front of the experimental section at distance piece configuration, and the experimental section of distance piece configuration adopts the structure be with and turned back, thus simulate the impact in the wall boundary layer of the precursor compression of distance piece upstream, and the present invention is by the adjustment of lip angle, inner passage height, afterbody throttling degree, thus under simulating different operating mode, the flow mechanism of distance piece is studied.
Description
Technical field
The present invention relates to aloof punching engine field, especially, relate to a kind of flow tunnel testing device of the wind tunnel test for aloof punching engine distance piece.
Background technology
Aircraft can be divided into by flying speed: subsonic flight device (Mach number <1), transonic speed aircraft (0.8< Mach number <1.2), supersonic aircraft (1< Mach number <5), hypersonic aircraft (Mach number >5) etc.Along with the raising of flying speed, conventional engine cannot be competent at the demand of hypersonic aircraft, at this moment there has been proposed the concept of scramjet engine, namely to burn in supersonic condition undertissue at engine interior oxidant gas and fuel and spray from aircraft afterbody, thus producing huge thrust.
As the major impetus device of Air-breathing hypersonic vehicle, scramjet engine and correlation technique thereof oneself become the frontline technology position that world community researchist competitively fights for.Research shows, if when flying speed reaches Mach more than 5. still adopt traditional sub-burning ramjet, will enter the flow slowing down of engine to subsonic speed, the high stagnation temperature height stagnation pressure of air-flow brings extreme difficulties by giving the thermal protection of material; High static temperature fails to be convened for lack of a quorum and causes firing chamber combustion product generation dissociation simultaneously, and dissociation will absorb a large amount of heat energy, causes burning capacity release efficiency low, and engine is difficult to produce positive thrust.The air-flow entering firing chamber should be allowed in this case still to keep supersonic speed, and in the burning of supersonic speed condition undertissue, Here it is scramjet engine.For rocket engine, a large advantage of Air-breathing hypersonic vehicle be exactly self without the need to carrying oxygenant, but utilize the oxygen tissue in air to burn.What the air intake duct in scramjet engine completed is exactly " air-breathing " this work.As the admission gear of scramjet engine, the effect of air intake duct be catch certain flow air-flow and deceleration supercharging is carried out to it, then flow to firing chamber, to ensure to organize burning smoothly in firing chamber.
As described above, be different from traditional sub-burning ramjet, Scramjet Inlet is caught, supercharging of slowing down, the air that is then supplied to firing chamber be still supersonic speed.Under being operated in hypersonic condition, so usually the air intake duct of scramjet engine is called hypersonic inlet.The quality of hypersonic inlet performance is all vital for the normal work of scramjet engine and whole aircraft.A good hypersonic inlet of design should have following feature: lightweight construction, compression efficiency are high, resistance is little, be supplied to the air-flow of firing chamber has high-quality (mainly referring to that uniform stream degree is high), wide Mach number requirement can be met (namely can have several characteristics above in certain range of Mach numbers), there is good firing chamber matching properties (under the duty that firing chamber is different, air intake duct can not by the impact in downstream).
The composition of scramjet engine includes air intake duct, distance piece, firing chamber and jet pipe.The effect of air intake duct is collected gas and carries out precompression to gas, makes gas deceleration, supercharging.Firing chamber is the place of gas and fuel generation supersonic combustion, and its inside exists High Temperature High Pressure, and the chemical energy of fuel is the mechanical energy of gas, and gas sprays aircraft and produces larger thrust after jet pipe accelerates afterwards.Distance piece is one section of gas passage between air intake duct and firing chamber, although its structure is simple, plays an important role.In distance piece, there is very complicated flow phenomenon after gas enters air intake duct, comprise shock wave, shock train, Shock/Boundary-Layer interaction, boundary-layer separation etc.Its effect is the high temperature and high pressure environment in isolation firing chamber, and the air intake duct preventing from causing thus blocking and engine do not start, and distance piece provides that gas slows down further, the place of supercharging in addition, is conducive to gas and fuel fully mixes, burns.
From structure, distance piece is one section of pipeline accepting air intake duct and firing chamber, but from aerodynamic angle, it is the place of ultrasonic gas generation Complex Phenomena in Vertical Bell Jar.Distance piece performance quality directly has influence on the performance of scramjet engine, and the therefore research work of distance piece, especially experimental study enjoys the concern of researcher and model department.The experimental study carrying out distance piece needs corresponding testing equipment essentially.From existing documents and materials, the scheme of design isolated section testing equipment is divided into two classes usually: a class is an independent design distance piece model be put in large-scale conventional wind tunnel test cabin, comes gas velocity and the flow phenomenon of distance piece inside in Reality simulation situation by existing conventional wind-tunnel; Another kind of distance piece parts that to be design one identical with existing conventional test chamber two ends flange size, and these parts are replaced original conventional test chamber, thus form an entirety with other parts of wind-tunnel and then for testing measurement.But all there is certain deficiency in this two schemes: the advantage of first kind scheme is that modelling is simple, cost is low, but distance piece is an independent model, it departs from other assembly of air intake duct, and internal flow and the truth of its simulation exist bigger difference; The advantage of Equations of The Second Kind scheme be by existing wind-tunnel can the air intake duct of analog isolation section upstream to a certain extent on the impact of distance piece, comparatively close with truth, but in this case, the geometric shape of distance piece is restricted, and cannot carry out the distance piece experimental study of a large amount of multi-states, multi-configuration.
Summary of the invention
The object of the invention is to provide a kind of supersonic speed distance piece flow tunnel testing device, cannot the impact in real simulation upstream inlet road and the technical matters that operating mode is limited, test efficiency is low of distance piece simulation to solve existing distance piece wind tunnel test.
For achieving the above object, the technical solution used in the present invention is as follows:
A kind of supersonic speed distance piece flow tunnel testing device, comprise: for collecting the gas collector of gas, the outlet of gas collector connects and is used for the stable section that stabilizing gas gatherer exports the air velocity distribution of gas, the outlet of stable section is connected with the supersonic nozzle section for accelerating air-flow velocity, the outlet of supersonic nozzle section is connected with the experimental section of the distance piece configuration for analog isolation section, and the diffuser of the air-flow in the experimental section of distance piece configuration through being connected with the outlet of the experimental section of distance piece configuration is discharged.
Further, the experimental section of distance piece configuration comprises: be Slab under the distance piece that the main body and geometric parameter of being with the pipeline configuration of turning back are adjustable, the lip plate that under distance piece, Slab comprises flat board and is rotationally connected with flat board, lip plate is provided with the first rotary rail assembly, correspondingly on flat board be provided with the second rotary rail assembly, on the faceted pebble that the rotation center of the first rotary rail assembly and the second rotary rail assembly is connected with flat board at lip plate, lip plate is fixed to installing plate through lip plate studdle, flat board is fixed to installing plate through adjusting screw(rod), installing plate is used for being fixedly connected with the bottom of main body and closing the bottom of main body.
Further, the side wall surface of main body and/or upper wall surface are provided with the view window for detecting optical experimental data, and view window adopts optical glass to make.
Further, the rear end of main body is provided with the throttling degree regulating device regulating afterbody throttling degree.
Further, throttling degree regulating device comprises screw rod, and the outside of main body is stretched out in one end of screw rod, and the other end of screw rod is positioned at the inside of main body and is connected with choke block, and choke block is positioned at dull and stereotyped top and relative with flat board.
Further, throttling degree regulating device also comprises the cover plate being provided with inner chamber, the upper wall surface of cover plate and main body is sealedly and fixedly connected, the threaded hole cooperation of screw rod through being positioned at the inner cavity top of cover plate extends into inner chamber, the card extender having one to be provided with through hole is run through in the end that screw rod is positioned at inner chamber, and choke block is fixedly connected with card extender, and the internal face of the through hole on card extender is shiny surface, by rotary screw, when not rotating card extender and choke block and then regulate the height of choke block.
Further, the experimental section of gas collector, stable section, supersonic nozzle section and distance piece configuration is all connected by flange seal between any two, and the height adjustable of flange.
Further, stable section comprises stable leading portion and stable back segment, stablize between leading portion with stable back segment and be connected by flange seal, and stable front intersegmental part is provided with the filter screen of the pulse characteristic for reducing the gas from gas collector, the pressure transducer that the internal face stablizing back segment is provided with for measurement gas air pressure is popped one's head in.
Further, gas collector is provided with the butterfly valve for controlling wind-tunnel opening and closing in porch.
Further, the internal face of supersonic nozzle section is plane in the horizontal direction, in vertical direction for being the curved surface first shrinking the trend distribution expanded afterwards, this curved surface adopts based on cubic spline curve configuration center line Mach number and adopts characteristic line method design.
The present invention has following beneficial effect:
Supersonic speed distance piece flow tunnel testing device of the present invention, by the front of the experimental section at distance piece configuration set gradually gas collector, stable section and, supersonic nozzle section, and the experimental section of distance piece configuration adopts the structure be with and turned back, thus simulate the impact in the wall boundary layer of the precursor compression of distance piece upstream, improve the experimental study level to the distance piece being applied to aloof punching engine, and supersonic nozzle section can be replaced according to testing requirements in the present invention, thus the test figure of distance piece under simulating different air-flow velocity.
Further, the experimental section of the distance piece configuration adopted in the present invention is the structure of Parameter adjustable, by the adjustment regulating the height of the angle of pitch of lip plate, dull and stereotyped height and choke block can realize lip angle to distance piece, inner passage height, afterbody throttling degree, thus flow mechanism research that is more convenient, that efficiently and economically carry out distance piece under different operating mode (different distance piece entrance, exit conditions).
Except object described above, feature and advantage, the present invention also has other object, feature and advantage.Below with reference to figure, the present invention is further detailed explanation.
Accompanying drawing explanation
The accompanying drawing forming a application's part is used to provide a further understanding of the present invention, and schematic description and description of the present invention, for explaining the present invention, does not form inappropriate limitation of the present invention.In the accompanying drawings:
Fig. 1 is the structural representation of the supersonic speed distance piece flow tunnel testing device of the preferred embodiment of the present invention;
Fig. 2 is the schematic top plan view of Fig. 1;
Fig. 3 is another structural representation of the supersonic speed distance piece flow tunnel testing device of the preferred embodiment of the present invention;
Fig. 4 is the structural representation of body Model under distance piece in the preferred embodiment of the present invention;
Fig. 5 is the perspective view of the supersonic speed distance piece flow tunnel testing device of the preferred embodiment of the present invention;
Fig. 6 is the close-up schematic view of region A in Fig. 5; And
Fig. 7 is the structural representation of throttling degree regulating device in the preferred embodiment of the present invention.
Embodiment
Below in conjunction with accompanying drawing, embodiments of the invention are described in detail, but the multitude of different ways that the present invention can be defined by the claims and cover is implemented.
See figures.1.and.2, the preferred embodiments of the present invention provide a kind of supersonic speed distance piece flow tunnel testing device, comprise: for collecting the gas collector 10 of gas, the outlet of gas collector 10 connects and is used for the stable section 20 that stabilizing gas gatherer 10 exports the air velocity distribution of gas, the outlet of stable section 20 is connected with the supersonic nozzle section 30 for accelerating air-flow velocity, the outlet of supersonic nozzle section 30 is connected with the experimental section 40 of the distance piece configuration for analog isolation section, the diffuser 50 of air-flow in the experimental section 40 of distance piece configuration through being connected with the outlet of the experimental section 40 of distance piece configuration is discharged.Wherein the experimental section 40 of distance piece configuration refers to the experimental section with similar distance piece internal geometrical characteristics form.The upstream components of flow tunnel testing device of the present invention owing to adopting the experimental section 40 of gas collector 10, stable section 20, supersonic nozzle section 30 and distance piece configuration to construct the inlet structure of analog isolation section upstream, thus make the experimental section 40 of distance piece configuration can the wind-tunnel flow mechanism of analog isolation section more realistically.
Preferably, with reference to Fig. 3 and Fig. 4, the experimental section 40 of distance piece configuration comprises: be Slab 42 under the distance piece that the main body 41 and geometric parameter of being with the pipeline configuration of turning back are adjustable, the pipeline configuration that main body 41 adopts band to transfer is the turnover in order to simulate in aloof punching engine between air intake duct and isolation road, make main body 41 closer to truth, the lip plates 421 that under distance piece, Slab 42 comprises flat board 422 and is rotationally connected with flat board 422, preferably, lip plate 421 is provided with the first rotary rail assembly 421a, on dull and stereotyped 422, the end adjacent with lip plate 421 is provided with the second rotary rail assembly 422a, the rotation center of the first rotary rail assembly 421a and the second rotary rail assembly 422a critically designs and processes at seam crossing, namely design on the faceted pebble that is connected with lip plate 421 dull and stereotyped 422.By coordinating of the first rotary rail assembly 421a and the second rotary rail assembly 422a, lip plate 421 can rotate up and down around with dull and stereotyped 422 faceted pebbles be connected, ensures not occur crack when rotating between lip plate 421 and flat board 422.Lip plate 421 is fixed on installing plate 423 through lip plate studdle 424, and dull and stereotyped 422 are fixed to installing plate 423 through adjusting screw(rod) 425, and installing plate 423 is for being fixedly connected with the bottom of main body 41 and closing the bottom of main body 41.Lip plate studdle 424 and adjusting screw(rod) 425 are all fixed through nut 426 and installing plate 423.Like this, by the control regulating the height of lip plate studdle 424 can realize the angle of pitch to lip plate 421, to control the size entering the lip angle of distance piece inside, the situation causing distance piece entrance lip angle to change when changing with simulated flight device flight attitude; Regulated by the height regulating the height of adjusting screw(rod) 425 can realize dull and stereotyped 422, and dull and stereotyped 422 form the structure of similar distance piece internal gas flow passage jointly with the upper wall surface 412 of main body 41 and the side wall surface 411 that is positioned at both sides, therefore by regulating the flat board height of 422 and the height of adjustable distance piece internal gas flow passage.
Preferably, with reference to Fig. 5 and Fig. 6, a throttling degree regulating device 43 is also provided with at the afterbody of main body 41, this throttling degree regulating device 43 comprises screw rod 431, the outside of main body 41 is stretched out in one end of screw rod 431, the other end of screw rod 431 is positioned at the inside of main body 41 and is connected with choke block 432, and choke block 432 is positioned at the top of dull and stereotyped 422 and 422 relative with dull and stereotyped.As shown in Figure 6, choke block 432 is pushed the inside of main body 41, relative to the flat board 422 of Slab under distance piece 42 to form throttling to flowing through middle air-flow.The height of gas passage is H, and the height that choke block 432 enters this gas passage is h, then throttling degree Δ=H/h is continuous variable under the adjustment of screw rod 431, can meet the demand that experimental study under different condition is arranged throttling degree.
With reference to Fig. 7, in a particular embodiment, throttling degree regulating device 43 comprises the cover plate 433 being provided with inner chamber 433a, the bottom of cover plate 433 is provided with seal groove 433c, seal groove 433c is sealedly and fixedly connected by the upper wall surface 412 of packing washer and main body 41, the threaded hole 433b cooperation of screw rod 431 through being positioned at the inner chamber 433a top of cover plate 433 extends into inner chamber 433a, the end that screw rod 431 is positioned at inner chamber 433a is run through a card extender 434, as shown in Figure 7, card extender 434 is provided with a through hole 434a, and the internal face of through hole 434a is shiny surface, screw rod 431 runs through through hole 434a, the bottom head of screw rod 431 is greater than through hole 434a, choke block 432 is fixedly connected with by multiple lock-screw 435 with card extender 434.The assembling mode of throttle regulator 43 is as follows: first card extender 434 is inserted in the bottom of screw rod 431, then with lock-screw 435, choke block 432 and card extender 434 are fixed, again choke block 432 and card extender 434 are pushed the inner chamber 433a of cover plate 433, screw rod 431 screws in the threaded hole 433b on cover plate 433, because screw rod 431 is only engaged with the threaded hole 433b on cover plate 433, by rotary screw 431, rotary motion is being converted to upper and lower rectilinear motion with under the cooperation of threaded hole 433b by screw rod 431, the card extender 434 and the choke block 432 that are positioned at screw rod 431 bottom then can not rotate along with the rotation of screw rod 431, only can do upper and lower rectilinear motion under the thrust of screw rod 431, cover plate 433 is sealed by the upper wall surface 412 placing packing washer and main body 41 in seal groove 433c, ensure that the impermeability requirement of whole wind tunnel experiment.
Because Slab under distance piece 42 simulates the inner structure of distance piece, and geometric parameter is adjustable, specifically comprises the adjustment of lip angle, gas passage and tail gas throttling degree, thus provides conveniently for carrying out at a high speed wind tunnel experiment under different operating mode efficiently; On the other hand, conveniently detecting optical data in process of the test, further, two side wall surfaces 411 of main body 41 offer the watch window for installing high-quality optical glass, due in actual applications, the pipeline of main body 41 for turning back, such as in a preferred embodiment, the place that turns back of main body 41 is from the horizontal by the angle of 16 degree, and optical glass is then difficult to be processed into band 16 degree of profiles of turning back, therefore the height of two of main body 41 side wall surfaces 411 is higher than upper wall surface 412.Preferably, the upper wall surface 412 of main body 41 also offers the installation window for installing difference in functionality upper plate, as upper wall surface 412 height of mounting strap wall pressure hole can spend organic glass upper plate thoroughly, this organic glass upper plate has 16 degree and turns back, and can be used in the pressure distribution measuring distance piece interior flow field simultaneously.In addition, if upper plate to be replaced with the optical glass of high-quality, then can be used for through laser, and then carry out NPLS (Nano-tracer Planar Laser Scattering, the scattering of nanometer spike planar laser) and test and obtain the fine structure image in distance piece flow field.
In a particular embodiment, with reference to Fig. 1, Fig. 3 and Fig. 5, the experimental section 40 of distance piece configuration and diffuser 50 are arranged on horizontal stand 60, the experimental section 40 of gas collector 10, stable section 20, supersonic nozzle section 30 and distance piece configuration is all connected by flange seal between any two, and the flange between gas collector 10, stable section 20 and supersonic nozzle section 30 is all fixed on by trimming rack 62 on the tilted supporter 61 that is positioned at inclined ramp on horizontal stand 60, supersonic nozzle section 30 is fixed on horizontal stand 60 by trimming rack 62.
Preferably, gas collector 10 is the pipeline of one section of circle side of turning, and entrance 11 is circular, and outlet 12 is that square, square size is consistent with the flange in downstream, and entrance 11 is with dish valve 13.Gas collector 10 Main Function collects gas using the source of the gas as downstream flow, can control operation and the closedown of whole wind-tunnel simultaneously.
Preferably, stable section 20 comprises stable leading portion 21 and stable back segment 22, stablize between leading portion 21 with stable back segment 22 and be connected by flange seal, and stablize the filter screen that leading portion 21 inside is provided with the pulse characteristic for reducing the gas from gas collector 10, the pressure transducer that the internal face stablizing back segment 22 is provided with for measurement gas air pressure is popped one's head in, to detect the stagnation pressure size before gas enters nozzle section.Although two sections of stable section length are not long, for air current flow, gas has enough been made to tend towards stability in the motion of inside.
Preferably, supersonic nozzle section 30 is two-dimensional ultrasound speed jet pipe, and internal face is plane in the horizontal direction, in vertical direction for being the curved surface 31 first shrinking the trend distribution expanded afterwards.Curved surface 31 carries out designing for the characteristic curve method for designing that have employed based on cubic spline curve configuration axis Mach Number Distribution.When gas enters supersonic nozzle section 30 inside, because upper and lower wall is in vertical direction in first shrinking the trend expanded afterwards, gas is constantly accelerated to supersonic speed from subsonic speed and sprays this section.Determine that the key of gas spouting velocity is this section of outlet height and the ratio of throat's (middle, be retracted to minimum place), determine that the factor of the homogeneity, stability etc. in the rear flow field of gas ejection is the method for designing of upper and lower wall.Very even, the actual Mach number in flow field (characterizing the dimensionless physical quantity of gas velocity) after adopting the upper and lower wall of this method design can ensure gas ejection reaches design Mach number 99%.And just can produce the air-flow of friction speed by changing different nozzle sections, with satisfied test needs.In addition, gas forms boundary layer and to the motion of downstream experimental section and development at nozzle section wall, can the precursor compressing surface boundary layer of Scramjet Inlet that is virtually reality like reality, makes this testing table closer to truth.
The workflow of supersonic speed distance piece flow tunnel testing device of the present invention is as follows:
A. gas enters test air tunnel through gas collector 10;
B. the gas exported through gas collector 10 is when flowing through stable leading portion 21 and stable back segment 22, and the isoparametric pulsation of the pressure of gas, speed, density reduces, and gas is more stable, is conducive to the stable flow process of generation for experimental study;
C. the gas exported through stable section 20 enters supersonic nozzle section 30, because the inwall upper lower wall surface in vertical direction of supersonic nozzle section 30 has the profile of first shrinking and expanding afterwards, gas acutely accelerates to supersonic speed when flowing through this section, and in concrete test, this supersonic nozzle section 30 can be replaced, and makes air-flow accelerate to different speed by replacing nozzle section;
D. the supersonic flow after accelerating enters the experimental section 40 of distance piece configuration, because this section adopts distance piece configuration, so supersonic flow there will be and flow field structure like real scramjet engine distance piece inner classes in the passage of this section;
E. by the distance piece flow field regulating lip angle, distance piece internal channel height, afterbody throttling degree can obtain different qualities, to meet the demand of experimental study;
F. last gas is discharged through the diffuser 50 of wind-tunnel afterbody.
Supersonic speed distance piece flow tunnel testing device of the present invention, by setting gradually gas collector 10, stable section 20 and supersonic nozzle section 30 in the front of the experimental section 40 of distance piece configuration, and the experimental section 40 of distance piece configuration adopts the structure be with and turned back, thus simulate the impact in the wall boundary layer of the precursor compression of distance piece upstream, improve the experimental study level to the distance piece being applied to aloof punching engine, and supersonic nozzle section 30 can be replaced according to testing requirements in the present invention, thus the test figure of distance piece under simulating different air-flow velocity.Further, the experimental section 40 of the distance piece configuration adopted in the present invention is the structure of Parameter adjustable, by the adjustment regulating the angle of pitch of lip plate 421, the dull and stereotyped height of 422 and the height of choke block 432 can realize lip angle to distance piece, inner passage height, afterbody throttling degree, thus flow mechanism research that is more convenient, that efficiently and economically carry out distance piece under different operating mode.
The foregoing is only the preferred embodiments of the present invention, be not limited to the present invention, for a person skilled in the art, the present invention can have various modifications and variations.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 (9)
1. a supersonic speed distance piece flow tunnel testing device, it is characterized in that, comprise: for collecting the gas collector (10) of gas, the outlet of described gas collector (10) connects and is used for stablizing the stable section (20) that described gas collector (10) exports the air velocity distribution of gas, the outlet of described stable section (20) is connected with the supersonic nozzle section (30) for accelerating air-flow velocity, the outlet of described supersonic nozzle section (30) is connected with the experimental section (40) for the distance piece configuration of analog isolation section, the diffuser (50) of air-flow in the experimental section (40) of described distance piece configuration through being connected with the outlet of the experimental section (40) of described distance piece configuration is discharged,
The experimental section (40) of described distance piece configuration comprises: be Slab (42) under the distance piece that the main body (41) and geometric parameter of being with the pipeline configuration of turning back are adjustable, the lip plate (421) that under described distance piece, Slab (42) comprises flat board (422) and is rotationally connected with described flat board (422), described lip plate (421) is provided with the first rotary rail assembly (421a), described flat board (422) is above corresponding is provided with the second rotary rail assembly (422a), on the faceted pebble that the rotation center of described first rotary rail assembly (421a) and described second rotary rail assembly (422a) is connected with described flat board (422) described lip plate (421), described lip plate (421) is fixed to installing plate (423) through lip plate studdle (424), described flat board (422) is fixed to installing plate (423) through adjusting screw(rod) (425), described installing plate (423) is for being fixedly connected with the bottom of described main body (41) and closing the bottom of described main body (41).
2. supersonic speed distance piece flow tunnel testing device according to claim 1, is characterized in that:
The side wall surface (411) of described main body (41) and/or upper wall surface (412) are provided with the view window for detecting optical experimental data, and described view window adopts optical glass to make.
3. supersonic speed distance piece flow tunnel testing device according to claim 1, is characterized in that:
The rear end of described main body (41) is provided with the throttling degree regulating device (43) regulating afterbody throttling degree.
4. supersonic speed distance piece flow tunnel testing device according to claim 3, is characterized in that:
Described throttling degree regulating device (43) comprises screw rod (431), the outside of described main body (41) is stretched out in one end of described screw rod (431), the other end of described screw rod (431) is positioned at the inside of described main body (41) and is connected with choke block (432), and described choke block (432) is positioned at the top of described flat board (422) and relative with described flat board (422).
5. supersonic speed distance piece flow tunnel testing device according to claim 4, is characterized in that:
Described throttling degree regulating device (43) also comprises the cover plate (433) being provided with inner chamber (433a), described cover plate (433) is sealedly and fixedly connected with the upper wall surface (412) of described main body (41), threaded hole (433b) cooperation of described screw rod (431) through being positioned at described inner chamber (433a) top of described cover plate (433) extends into described inner chamber (433a), the card extender (434) having one to be provided with through hole (434a) is run through in the end that described screw rod (431) is positioned at described inner chamber (433a), described choke block (432) is fixedly connected with described card extender (434), the internal face of the described through hole (434a) on described card extender (434) is shiny surface, by rotating described screw rod (431), when not rotating described card extender (434) and described choke block (432) and then regulate the height of described choke block (432).
6. supersonic speed distance piece flow tunnel testing device according to claim 1, is characterized in that:
The experimental section (40) of described gas collector (10), stable section (20), supersonic nozzle section (30) and distance piece configuration is all connected by flange seal between any two, and the height adjustable of described flange.
7. supersonic speed distance piece flow tunnel testing device according to claim 1, is characterized in that:
Described stable section (20) comprises stable leading portion (21) and stable back segment (22), be connected by flange seal between described stable leading portion (21) with described stable back segment (22), and described stable leading portion (21) inside is provided with the filter screen of the pulse characteristic for reducing the gas from described gas collector (10), the pressure transducer that the internal face of described stable back segment (22) is provided with for measurement gas air pressure is popped one's head in.
8. supersonic speed distance piece flow tunnel testing device according to claim 1, is characterized in that:
Described gas collector (10) is provided with the butterfly valve (13) for controlling wind-tunnel opening and closing in porch.
9. supersonic speed distance piece flow tunnel testing device according to claim 1, is characterized in that:
The internal face of described supersonic nozzle section (30) is plane in the horizontal direction, in vertical direction for being the curved surface (31) first shrinking the trend distribution expanded afterwards, this curved surface (31) adopts based on cubic spline curve configuration center line Mach number and adopts characteristic line method design.
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| CN112555027B (en) * | 2020-12-12 | 2022-07-12 | 西北工业大学 | Self-adaptive control method for shock wave seal of hypersonic air inlet |
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