CN114791348A - S-shaped flow channel flow control variable parameter testing system - Google Patents

Abstract

The invention discloses an S-shaped flow channel active flow control variable parameter testing system, which comprises a bending section and a straight section connected with two ends of the bending section, wherein a replaceable inserting plate is detachably arranged on the bending section, and an installing groove is formed in the replaceable inserting plate at a position to be tested; the replaceable fluid oscillator is arranged in the mounting groove and detachably connected with the mounting groove; the jet flow outlet of the replaceable fluid oscillator faces the inner flow channel of the bending section; the system can realize the replacement of the position to be tested by replacing the replaceable inserting plate and the mounting grooves at different positions on the replaceable inserting plate, and simultaneously realize the change of factors such as jet angle, exciter quantity, space and the like by replacing the replaceable fluid oscillator, so that the system can quickly and conveniently adjust various influence parameters influencing the active flow control inside the S-shaped air inlet channel.

Description

S-shaped flow channel flow control variable parameter testing system

Technical Field

The invention relates to the technical field of active flow control, in particular to an S-shaped flow channel flow control variable parameter testing system.

Background

With the improvement of the design technology of fighters, the viability of modern fighters is concerned more and more, and the stealth performance is a non-negligible item in the modern fighters. The engine is used as a main heat emission part of the fighter, the shielding degree of the part of the fighter influences the stealth performance to a great extent, the S-shaped air inlet channel can shield the engine blade to a certain degree due to the unique structure of the S-shaped air inlet channel, and the reflecting surface for radar monitoring can be effectively reduced, so that the S-shaped air inlet channel becomes one of solutions of the problem and is widely applied to various places such as stealth fighters, unmanned aerial vehicles and the like in development.

However, it has been found in research that the geometric features of the S-shaped inlet also tend to complicate the internal flow field thereof. A strong back pressure gradient exists in a large-curvature bending section, and finally a flow separation phenomenon is caused, so that the total pressure recovery coefficient of the outlet section of the air inlet passage is reduced, and the integral effective thrust of the engine is reduced. At the same time, the flow separation phenomenon will also cause a large total pressure distortion and secondary rotational flow at the outlet cross section of the air inlet, which may induce the surge of the engine. In order to increase the working range and working efficiency of the engine and further improve the performance of the warplane, it is necessary to effectively control the separation flow of the S-shaped air inlet channel and improve the flow field quality of the outlet of the air inlet channel by a passive or active flow control means.

The most common passive flow control scheme is a vortex generator, which interacts a series of fluid structures such as spontaneously induced vortices with the boundary layer at a suitable position in the pipe, which accelerates the exchange of energy inside the boundary layer, thereby achieving the purpose of suppressing the boundary layer separation. However, this control method, although simple in construction, generally only performs well under certain operating conditions. The active flow control scheme has a relatively complex structure, can be actively adjusted according to actual working conditions, and has good variable working condition performance, so that the active flow control scheme which is reasonably designed is an ideal and feasible control scheme for the fighter with variable operating conditions.

External disturbance and energy injection are required to be introduced in the active flow control, compared with a steady-state blowing/inhaling method, the active flow control method based on periodic unsteady-state excitation is higher in efficiency, the efficiency can be improved by two orders of magnitude by calculating with an additional momentum coefficient, and the method is verified in application research in various fields. These periodic unsteady-state perturbations are generated by a variety of actuators, with synthetic jet actuators, plasma actuators, fluidic oscillators, and the like being more typical. However, the operating conditions in the aircraft engine are severe, the reliability requirements on all parts are extremely high, and the difficulty of using unsteady flow control is lack of an exciter with simple structure and high reliability.

A fluidic oscillator is an active control device that inputs a source of gas at a given pressure at an inlet and produces a periodic oscillating jet at an outlet. The device has the advantages of no movable part, simple structure, large flow quantity at the outlet, self-oscillation, self-excitation maintenance and the like, thereby greatly arousing the interest of researchers.

At present, the test and analysis of the jet oscillator are more applied to outflow, however, for the control problem in the aspect of flow separation inside the S-shaped air inlet channel, the application and test scheme of the jet oscillator still needs to be further improved. Due to the small size of the exit of the fluidic oscillator itself, the area of influence is limited, whereas the controlled area is generally large by comparison. In order to apply fluidic oscillators to practical flow separation control scenarios, a series of arrays of fluidic oscillators need to be arranged within the flow region to be controlled. Thus, a series of discrete periodic oscillating jet excitations are formed at the surface of the controlled area. The design of the inner flow passage of the fluid oscillator is combined with the wall surface of the air inlet passage, a high-pressure air source is introduced from the outside or the interior of the aeroengine, and the required oscillating jet flow working frequency and amplitude are formed at the outlet of the oscillator by adjusting the pressure at the inlet of the flow passage of the fluid oscillator, so that the reduction of the flight resistance and the size of the air inlet passage of the airplane and the great improvement of the working margin of the engine are realized simultaneously on the premise of not increasing the structural complexity of the existing airplane and not reducing the reliability and the safety of the existing airplane. The active control technology for flow separation in the S-shaped air inlet channel based on the active excitation of the self-excited oscillation jet flow combines the advantages of high active flow control efficiency and high reliability/safety of passive flow control, and obtains a good effect of active control in a passive control mode. The flow loss of the S-shaped air inlet channel can be obviously reduced, the quality of the air flow at the inlet of the engine is improved, the safety, the reliability and the complexity of the system structure are considered, and the method has a wide prospect in practical engineering application.

The active regulation and control effect of the flow in the S-shaped air inlet channel is closely related to the position of jet excitation, the excitation angle, the distribution position of the exciters, the number of the exciters, the speed and the frequency of the excitation jet. However, once the design geometry of the fluidic oscillator is determined, the frequency response characteristic and the speed response characteristic of the fluidic oscillator along with the change of the inlet pressure are also determined when the working medium characteristic is unchanged. The excitation speed and frequency can only be adjusted by adjusting the inlet pressure. In order to quantitatively research the influence of the different excitation parameters on the flow quality in the S-shaped air inlet channel/flow channel, a large amount of parametric experimental research needs to be carried out, wherein the influence comprises the influence of a jet flow excitation position, an excitation angle, the number of the exciters and the distribution position of the exciters besides the excitation speed and the frequency. Each group of parameter combination requires a complex flow channel with a plurality of fluidic oscillators processed on the wall surface of the S-shaped air inlet channel, which results in excessively high test cost and excessively long test period.

Disclosure of Invention

In order to solve the defects in the prior art, the application provides an S-shaped flow channel flow control variable parameter testing system, various design parameters and machining precision requirements can be met through modular design, convenience is improved, and meanwhile the accuracy of a test is guaranteed.

The technical scheme adopted by the invention is as follows:

an S-shaped flow channel flow control variable parameter testing system comprises:

the bending section is provided with a bending part,

the replaceable inserting plate is arranged on the bending section and detachably mounted on the bending section;

arranging a mounting groove on the replaceable plugboard at the position to be tested;

the replaceable fluid oscillator is mounted in the mounting groove, the replaceable fluid oscillator is detachably connected with the mounting groove, and a jet flow outlet of the replaceable fluid oscillator faces to the inner flow channel of the bending section;

and the straight sections are arranged at two ends of the bent section and are smoothly connected with the inside of the bent section.

Furthermore, a plurality of replaceable insertion plates are arranged at each position on the bending section, a part of the replaceable insertion plates are not provided with installation grooves, and the other part of the replaceable insertion plates are provided with installation grooves at different positions.

Further, a single test site, or a plurality of test sites, is provided at the curved section.

Further, the replaceable fluidic oscillator comprises a connecting part and an upper convex part on the upper part of the connecting part, wherein the upper convex part is a bump with a slope; the jet outlets of the oscillator array in the interchangeable fluidic oscillator are disposed on the upper surface of the upper protrusion.

Further, the mounting groove is a slope groove matched with the upper convex part, and the upper convex part is buckled with the mounting groove; the connecting part is detachably connected with the replaceable inserting plate through a connecting piece.

Furthermore, the adjacent replaceable plugboards and the adjacent straight sections are designed into mutually matched ladder shapes, and then are detachably connected by utilizing connecting pieces.

Further, an oscillator array is arranged in the replaceable fluid oscillator, an included angle between the jet flow spraying direction of the oscillator array and the internal flow channel is alpha, and the value range of the alpha is 15-90 degrees.

Further, the jet exit positions of the oscillator arrays for different jet angles are the same.

Further, the oscillator array employs a relaxation type oscillator, a sonic type oscillator, a coanda sweep type oscillator, or a jet coupled type oscillator.

Further, the replaceable fluid oscillator is composed of an oscillator mounting side and a cover plate, an oscillator array is arranged on the oscillator mounting side 7, and the oscillator mounting side is fixedly connected with the cover plate.

Further, the replaceable fluidic oscillator is formed by CNC precision machining, integrated 3D printing or other forming modes.

Advantageous effects

1. The invention provides an S-shaped flow channel flow control variable parameter testing system, which adopts a double replaceable structure of a replaceable plug board and a replaceable fluid oscillator array; the excitation position of the oscillator can be changed by changing the position of the buckling groove on the replaceable inserting plate, so that the influence of the active excitation position on the control effect can be researched. The influence of different re-excitation position parameters on the active control can be researched on the premise of not changing the original S-shaped flow channel structure and the structure of the oscillator array only by replacing the plug board and ensuring the shape component of the buckling groove. The multivariable research is realized, the cost of parameter research is saved, and the economical efficiency and the experimental efficiency are improved.

On the same replaceable plug board, by changing different fluid oscillator arrays, namely changing the number of the fluid oscillators, the size of the oscillators, the distribution spacing of the oscillators, the types of the oscillators, different jet excitation angles and the like on different arrays, the influence rule of different excitation parameters on the flow control efficiency is researched.

2. The replaceable plug board is connected with the S-shaped flow channel in a stepped buckling mode, and the buckling surface is connected and sealed through the sealing ring and the fastening bolt, so that gas leakage caused by machining errors and installation accuracy is avoided.

3. The exciter array is connected with the plug board in a buckling mode through the buckling groove with the slope, the slope structure can achieve quick buckling of the exciter array, and installation of the large-angle oscillator in a narrow size is guaranteed. The design of the oscillator array and the buckling surface of the replaceable plugboard is not vertical, but a slope design determined according to the control jet angle is used, so that the oscillator array can be conveniently and quickly assembled and disassembled, and meanwhile, the installation gap is reduced, and gas leakage is avoided.

4. In order to research the influence of the included angle between the jet flow direction of the oscillator and the incoming flow direction, fluid oscillator arrays with different inclination angles need to be manufactured, and the replaceable fluid oscillators with different jet flow types and different jet flow angles are consistent with the assembly surface of the mounting groove on the insert plate; and the outlet jet flow positions of the arrays with different angles are ensured to be consistent.

5. The test system can meet various design parameters and machining precision requirements through modular design, convenience is improved, and meanwhile accuracy of the test is guaranteed.

6. Carry out symmetry fastening and sealed through countersunk head bolt to the exciter, make it can realize the exciter control test of multiple angle to reduced machining error's influence and processing defect to the influence of result, no longer had specific requirement to the section material of testing simultaneously, metal working or 3D print the part and all can reach comparatively ideal effect.

Drawings

FIG. 1 is a schematic structural diagram of an S-shaped flow channel flow control variable parameter testing system of the present invention;

FIG. 2 is a schematic view of a replaceable insert plate;

FIG. 3 is a schematic view of a replaceable actuator configuration;

FIG. 4 is a schematic view of the assembly of the interchangeable exciter, interchangeable insert plate and S-shaped runner wall;

FIG. 5 is a schematic view of a replaceable actuator configuration;

FIG. 6 is a schematic view of a 45 angle interchangeable exciter configuration;

FIG. 7 is a schematic view of a 90 angle interchangeable exciter configuration;

FIG. 8 is a schematic view of a 45 angle interchangeable exciter configuration and a 90 angle interchangeable exciter in a folded configuration;

FIG. 9 is a schematic view of the interchangeable exciter assembled with the interchangeable insert plate;

FIG. 10 is a schematic diagram of an oscillator array within a replaceable exciter;

FIG. 11 is an array of four different configurations of fluidic oscillators; (a) a relaxation type oscillator; (b) a sonic oscillator; (c) a coanda swept type oscillator; (d) a jet coupled oscillator;

FIG. 12 is a schematic view of the replaceable fluidic oscillator fixedly attached from the outside and fixedly attached from the inside;

in the figure, 1, a bending section, 2, an inlet straight section, 3, an outlet straight section, 4, a replaceable insert plate, 4a, a first replaceable insert plate, 4b, a second replaceable insert plate, 5, a mounting groove, 6, a replaceable fluid oscillator, 6-1, an upper convex part, 6-2, a connecting part, 6-3, a lower convex part, 6-4, a jet outlet, 6-5, an outer connecting hole, 6-6, an inner connecting hole, 7, an oscillator mounting side, 8, a cover plate, 9, an oscillator, 10 and a countersunk hole.

Detailed Description

In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.

Aiming at the defects in the prior art, the invention designs an S-shaped flow channel flow control variable parameter testing system as shown in figure 1, which comprises a bending section 1 and a straight section which are connected.

In the present embodiment, the cross section of the S-shaped flow path is designed to be rectangular, but the cross section is not limited to this shape, and may be various shapes such as circular.

In this embodiment, the S-shaped flow channel with a rectangular cross section is further described as follows:

the straight section comprises an inlet straight section 2 and an outlet straight section 3, flanges are respectively arranged on the outermost sides of the inlet straight section 2 and the outlet straight section 3, and the inlet straight section 2 flows through a flange wind tunnel to provide inflow conditions required by the experiment for the S-shaped runner flow control experiment; the outlet straight sections 3 are respectively connected with an output pipeline by flanges.

The inlet straight section 2 and the outlet straight section 3 are respectively arranged at two sides of the bent section 1, and the bent section 1 is smoothly connected with an internal flow passage formed by the inlet straight section 2 and the outlet straight section 3. The bending section 1 is an experimental section and generates flow structures such as flow separation and flow direction vortex.

More specifically, the bending section 1 can be made of various materials such as metal and organic glass plates, and can be machined in various manners such as machining and laser cutting.

The bending section 1 is formed by smoothly connecting a plurality of replaceable insert plates 4 to form an S-shaped flow passage. As seen from fig. 1, the replaceable insert plates 4 of the upper and lower parts of the bending section 1 are curved like the two replaceable insert plates 4 of the upper part are reversely bent, thereby forming an S-shape after being connected, the two replaceable insert plates 4 of the lower part are designed in the same way, and the S-shapes formed by connecting the upper and lower parts are parallel to each other to form an S-shaped flow passage. Along the flow direction a smooth connection between two interchangeable insert plates 4 connected to each other is required to ensure that the flow channel interior is smooth. The side wall interchangeable insert plate 4 is also S-shaped.

The system designed by the application is used for testing the active regulation control effect of the internal flow of the S-shaped air inlet channel, and the factors influencing the active regulation control effect are closely related to the position of jet stimulation, the stimulation angle, the distribution position of the stimulators, the number of the stimulators, the speed and the frequency of stimulation jet. In order to be able to carry out changes and quantitative investigations of the above-mentioned parameters in the same test system, the present application therefore envisages a replaceable insert plate 4 in the bending section 1. Referring to fig. 4, the adjacent replaceable insert plates 4 and the replaceable insert plate 4 and the adjacent straight sections are designed to be mutually matched in a stepped shape, and the replaceable insert plates 4 can be detachably mounted from the outside by using connecting pieces such as screws while being quickly positioned by using the mutual matching of the stepped structures. As shown in figure 4, the connecting part between the left end of the replaceable inserting plate 4 and the inlet straight section 2 is in a step shape, and is locked from the outside by using screws after being matched with each other, and when the replaceable inserting plate 4 needs to be replaced, the replaceable inserting plate can be directly detached. The connecting part of the right end of the replaceable inserting plate 4 and the other replaceable inserting plate 4 is designed into a ladder shape, and the replaceable inserting plates are matched with each other and then locked from the outside by screws. The screw is locked from the outside, so that the screw is convenient to install, meanwhile, the screw cannot extend to the internal flow passage, and the smoothness of the internal flow passage is guaranteed.

According to the replaceable flow oscillator, the mounting groove 5 is formed in the replaceable inserting plate 4, the replaceable flow oscillator 6 is mounted on the mounting groove 5, and the jet outlet 6-4 of the replaceable flow oscillator 6 faces the flow channel and is arranged in the flow channel. In order to enable the exchangeable fluidic oscillator 6 to be replaced, the exchangeable fluidic oscillator 6 is detachably mounted in the mounting slot 5 in this application, in order to facilitate the exchange of exchangeable fluidic oscillators 6 of different jet types and different jet angles.

More specifically, in order to be able to change the test position of the interchangeable fluidic oscillator 6, the interchangeable insert plate 4 is provided with a plurality of pieces at each position on the curved section 1, and a portion of the interchangeable insert plate 4 is not provided with the mounting groove 5, and a different position of the other portion of the interchangeable insert plate 4 is provided with the mounting groove 5. When the test position needs to be changed, only one replaceable inserting plate 4 with different mounting groove 5 positions needs to be replaced. For example, in fig. 1, the mounting groove 5 is formed on the uppermost portion of the first interchangeable insert board 4a, and when other positions of the first interchangeable insert board 4a need to be tested, only another first interchangeable insert board 4a with the mounting groove 5 formed on a different position needs to be replaced, so as to change the testing position of the interchangeable fluidic oscillator 6, and the rest parts are the same. Because in this application just can realize the regulation to test position, efflux type, efflux angle through removable picture peg and change removable fluidic oscillator 6, test system's overall structure is unchangeable, need not design the test system that appears to every kind of change, so can reduce test cost, and through quick replacement, can carry out many times experimental, shortened test period.

More specifically, the system can also test a plurality of positions simultaneously, for example, in fig. 1, an upper first interchangeable insert plate 4a and a lower second interchangeable insert plate 4b can be replaced simultaneously by a replaceable insert plate having a mounting groove 5, and the mounting groove 5 is provided with a replaceable fluid oscillator 6; it is possible to perform a test at the first interchangeable insert board 4a, the lower second interchangeable insert board 4b at the same time.

More specifically, when replaceable fluidic oscillators 6 of different jet types and different jet angles need to be tested at the same test position, replaceable fluidic oscillators 6 of different jet types and different jet angles need to be replaced; but it is necessary to ensure that the position of the jet outlet 6-4 of the replaceable fluidic oscillator 6 is the same before and after replacement. To address this problem, the present application is implemented by optimizing the structure of the replaceable fluidic oscillator 6 and the mounting groove 5. With reference to fig. 2 and 3, the mounting groove 5 is a groove with a slope, the section of the mounting groove 5 is trapezoidal, the connecting portion between the replaceable fluid oscillator 6 and the mounting groove 5 is an upper convex portion 6-1, the upper convex portion 6-1 is a cube with a slope, and the rapid positioning between the upper convex portion 6-1 and the mounting groove 5 can be realized through the matching of the slope surface of the upper convex portion 6-1 and the slope surface of the mounting groove 5. Meanwhile, the positions of the jet outlets 6-4 of the replaceable fluid oscillators 6 with different jet types and different jet angles are the same; as shown in fig. 9, the center lines of the jet outlets 6-4 of all the replaceable fluidic oscillators 6 are at the same distance from the rear edge (divided into the front edge and the rear edge in the flow direction) of the mounting groove 5.

More specifically, the interchangeable fluidic oscillator 6 is detachably connected to the first interchangeable insert plate 4a in which the mounting groove 5 is located. As shown in fig. 5, the exchangeable fluid oscillator 6 includes a connection portion 6-2 and an upper projection 6-1 on an upper portion of the connection portion 6-2, and the connection portion 6-2 is detachably connected to the exchangeable insert plate 4 by a connection member such as a screw. The lower convex part 6-3 is internally provided with an oscillator array.

More specifically, the replaceable fluidic oscillator 6 is of a two-layer assembly type, the replaceable fluidic oscillator 6 is composed of an oscillator mounting side 7 and a cover plate 8, the oscillator mounting side 7 is provided with an oscillator array as shown in fig. 10, and the oscillator mounting side 7 and the cover plate 8 are fixedly connected.

More specifically, the replaceable fluidic oscillator 6 may be CNC precision machined, 3D print-in-one, or other molding.

More specifically, the oscillator array may employ a relaxation type oscillator, a sonic type oscillator, a coanda sweep type oscillator, or a fluidic coupling type oscillator as shown in fig. 11. The structural size and the arrangement spacing of the oscillator array are more expandable under the design scheme. The oscillator array requiring precision machining can be performed in various manners such as metal machining and 3D printing. Compared with the traditional experimental scheme, the size of a precision machining structure is reduced, the defect that the machining precision of a large structural part is insufficient is avoided, and the precision of a runner structure matching experiment with lower machining precision is ensured.

More specifically, the jet angle of the oscillator array is an included angle alpha between the jet direction of the oscillator array and the incoming flow direction, alpha can be changed between 15 degrees and 90 degrees, and the change of the alpha angle can generate different flow control effects. As shown in fig. 6, 7 and 8, wherein fig. 6 shows a 45 ° tilt angle array and fig. 7 shows a 90 ° tilt angle array, for the sake of clarity, the positions of the jet outlets 6-4 of the replaceable fluidic oscillators 6 with different jet angles are the same, and in conjunction with fig. 8, the two replaceable fluidic oscillators 6 in fig. 6 and 7 are overlapped, and it can be seen that the upper protrusions 6-1 of the two replaceable fluidic oscillators 6 are completely overlapped.

More specifically, in the actual assembly process, the replaceable fluidic oscillator 6 may be installed in a fixed manner from the outside or fixed from the inside according to the installation direction of the connection member between the replaceable fluidic oscillator 6 and the replaceable insert plate 4, depending on the installation position of the replaceable fluidic oscillator 6 and the structure of the replaceable fluidic oscillator 6, and depending on the connection manner between the replaceable fluidic oscillator 6 and the replaceable insert plate 4.

For two interchangeable fluidic oscillators 6 as shown in fig. 6 and 7, if the width of the connecting part 6-2 of the interchangeable fluidic oscillator 6 is sufficient and the connecting part 6-2 fits well with the interchangeable insert plate 4 where it is to be mounted, as shown in area a of fig. 12; for the connection between the replaceable fluid oscillator 6 and the replaceable insert plate 4 at the area A through a connecting piece such as a bolt, the bolt is connected from the outside of the whole flow passage to the inside of the flow passage, and the bolt sequentially passes through an external connecting hole 6-5 on the connecting part 6-2 and a connecting hole at the replaceable insert plate 4 to realize the connection of the two; a plurality of the external connecting holes 6-5 are uniformly arranged on the connecting part 6-2 and are also installed from the outside to the inside through bolts; at this time, the connecting holes corresponding to the external connecting holes 6-5 on the replaceable inserting plate 4 are blind holes, namely, the bolts cannot extend into the flow channel, so that the smoothness of the flow channel can be ensured.

However, the width of the connecting portion 6-2 is not enough for installing the fastener, and the radian exists between the connecting portion 6-2 and the replaceable insert plate 4 to be installed, so that the connecting portion cannot be well attached to the region B in fig. 12 (or the connecting portion 6-2 on the left side in fig. 6, the installation condition from the outside to the inside of the fastener), in this case, if the region B still adopts the connection mode from the outside to the inside in the region a, the connecting portion 6-2 on the region B cannot be uniformly distributed around the connecting member, the asymmetric bolt fastening easily causes gaps and local deformation, and the gaps and local deformation also cause various problems such as gas leakage and flow field distortion, and the experimental result is affected. In order to solve a problem, the invention adopts a mode that a connecting piece is arranged from the inner part of the flow channel to the outer part of the flow channel for the area B. A plurality of counter bores 10 are formed in the surface, located in the flow channel, of the replaceable insert plate 4 in the area B, as shown in fig. 9, and the plurality of counter bores 10 are uniformly arranged along the side edge of the jet flow outlet 6-4; a plurality of inner connecting holes 6-6 are uniformly arranged on the connecting part 6-2, and the inner connecting holes 6-6 correspond to the counter bores 10 one by one; when mounting, a connecting member such as a bolt is inserted from the counterbore 10 into the internal connecting hole 6-6 corresponding to the counterbore 10 to effect connection between the replaceable insert plate 4 and the replaceable fluidic oscillator 6. Because the counter sink 10 is provided with the replaceable insert plate 4 on the surface in the runner, the counter sink 10 will destroy the smoothness of the runner, and in order to ensure the smoothness of the runner in the area B, after the bolt is installed, gypsum and other materials are used as fillers to fill and level the counter sink 10.

In addition, the inner connection hole 6-6 and the outer connection hole 6-5 formed on the same side of the connection portion 6-2 need to be staggered by a certain distance and cannot be overlapped, as shown in the left side of fig. 3, fig. 3 only shows the schematic of the inner connection hole 6-6 and the outer connection hole 6-5 on the connection portion 6-2 on the left side, and in actual use, the inner connection hole 6-6 and the outer connection hole 6-5 on the connection portion 6-2 on the right side can also be arranged in this way.

The connection of the replaceable fluidic oscillator 6 to the replaceable insert plate 4 described above can balance the stresses on both sides of the oscillator array well, avoiding warping, gaps and local deformations, thus ensuring the characteristics of the main flow. After the fastening bolt is installed on one side of the main flow channel, the bolt hole is filled with fillers such as sealant, and the influence of local gaps and deformation on the flow field can be avoided.

The above embodiments are only used for illustrating the design idea and features of the present invention, and the purpose of the present invention is to enable those skilled in the art to understand the content of the present invention and implement the present invention accordingly, and the protection scope of the present invention is not limited to the above embodiments. Therefore, all equivalent changes and modifications made in accordance with the principles and concepts disclosed herein are intended to be included within the scope of the present invention.

Claims (11)

1. The utility model provides a S type runner flow control becomes parameter testing system which characterized in that includes:

a bending section (1) is arranged on the upper surface of the base,

the replaceable insert plate (4) is arranged on the bending section (1), and the replaceable insert plate (4) is detachably arranged on the bending section (1);

arranging a mounting groove (5) on the replaceable inserting plate (4) at the position to be tested;

the replaceable fluid oscillator (6) is installed in the installation groove (5), the replaceable fluid oscillator (6) is detachably connected with the installation groove (5), and a jet flow outlet of the replaceable fluid oscillator (6) faces to an internal flow channel of the bending section (1);

the straight sections are arranged at two ends of the bent section (1) and are smoothly connected with the inside of the bent section (1).

2. The S-shaped flow channel flow control variable parameter testing system as claimed in claim 1, wherein the replaceable insert plate (4) at each position on the bending section (1) is provided with a plurality of pieces, one part of the replaceable insert plate (4) is not provided with the mounting groove (5), and the other part of the replaceable insert plate (4) is provided with the mounting groove (5) at different positions.

3. The S-shaped flow channel flow control variable parameter testing system as claimed in claim 1, wherein a single testing position or a plurality of testing positions are provided at the bending section (1).

4. The S-shaped flow channel flow control variable parameter testing system as claimed in claim 1, wherein the replaceable fluidic oscillator (6) comprises a connection part (6-2) and an upper convex part (6-1) at the upper part of the connection part (6-2), the upper convex part (6-1) is a bump with a slope;

jet outlets (6-4) of an oscillator array in the replaceable fluidic oscillator (6) are arranged on the upper surface of the upper protrusion (6-1).

5. The S-shaped flow channel flow control variable parameter testing system as claimed in claim 4, wherein the mounting groove (5) is a groove with a slope matched with the upper convex part (6-1), and the upper convex part (6-1) is connected with the mounting groove (5 in a buckling way;

the connecting part (6-2) is detachably connected with the replaceable inserting plate (4) through a connecting piece.

6. The S-shaped flow channel flow control variable parameter testing system as claimed in claim 4, wherein the adjacent replaceable insert plates (4) and the adjacent straight sections are designed into mutually matched ladder-shaped shapes and are detachably connected by connecting pieces.

7. The S-shaped flow channel flow control variable parameter testing system according to claim 4, wherein an oscillator array is arranged in the replaceable fluidic oscillator (6), an included angle between the jet flow spraying direction of the oscillator array and the internal flow channel is alpha, and the value range of alpha is 15-90 degrees.

8. The S-shaped flow channel flow control variable parameter testing system as claimed in claim 4 or 7, wherein the positions of the jet outlets (6-4) of the oscillator arrays with different jet angles are the same.

9. An S-shaped flow channel flow control variable parameter testing system according to any one of claims 1-7, wherein the oscillator array is a relaxation oscillator, a sonic oscillator, a coanda sweep oscillator or a fluidic coupling oscillator.

10. The S-channel flow control variable parameter test system according to claim 9, wherein said replaceable fluidic oscillator (6) is formed by an oscillator mounting side (7) and a cover plate (8), the oscillator mounting side (7) is provided with an array of oscillators, and the oscillator mounting side (7) and the cover plate (8) are fixedly connected.

11. The S-channel flow control variable parameter testing system of claim 9, wherein the replaceable fluidic oscillator (6) is formed by CNC precision machining, integrated 3D printing, or other forming methods.

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