CN114791348B - S-shaped runner flow control variable parameter test system - Google Patents
S-shaped runner flow control variable parameter test systemInfo
- Publication number
- CN114791348B CN114791348B CN202210440712.XA CN202210440712A CN114791348B CN 114791348 B CN114791348 B CN 114791348B CN 202210440712 A CN202210440712 A CN 202210440712A CN 114791348 B CN114791348 B CN 114791348B
- Authority
- CN
- China
- Prior art keywords
- replaceable
- oscillator
- flow control
- jet
- control variable
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/02—Details or accessories of testing apparatus
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
本发明公开了一种S型流道主动流动控制变参数测试系统，包括弯曲段，以及弯曲段两端连接的平直段，在弯曲段可拆卸安装可更换插板，且在待测试位置处的可更换插板上设置安装槽；在安装槽内安装可更换流体振荡器，可更换流体振荡器与安装槽之间可拆卸连接；可更换流体振荡器的射流出口朝向弯曲段内部流道；本系统通过更换可更换插板、以及可更换插板上不同位置的安装槽可以实现对待测试位置的更换，同时通过更换可更换流体振荡器实现对射流角度、激励器数量、间距等因素的改变，因此本系统能够快速、方便的调节影响S型进气道内部主动流动控制的各种影响参数。
The present invention discloses an S-shaped flow channel active flow control variable parameter testing system, comprising a curved section and straight sections connected at both ends of the curved section, wherein a replaceable plug-in plate is detachably installed on the curved section, and a mounting slot is provided on the replaceable plug-in plate at a position to be tested; a replaceable fluid oscillator is installed in the mounting slot, and the replaceable fluid oscillator is detachably connected to the mounting slot; the jet outlet of the replaceable fluid oscillator faces the flow channel inside the curved section; the system can realize the replacement of the position to be tested by replacing the replaceable plug-in plate and the mounting slots at different positions on the replaceable plug-in plate, and simultaneously realize the change of factors such as the jet angle, the number of actuators, and the spacing by replacing the replaceable fluid oscillator, so that the system can quickly and conveniently adjust various influencing parameters affecting the active flow control inside the S-shaped air inlet channel.
Description
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 fighter plane design technology, the survivability of modern fighter plane is increasingly concerned, and stealth performance is a non-negligible item. The engine is used as a main heat emission part of the fighter, the stealth performance is greatly influenced by the shielding degree of the part, 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 the S-shaped air inlet channel is one of the solutions of the problem and is widely applied to various parts of stealth fighter, unmanned aerial vehicles and the like in various researches.
However, the geometric features of the S-shaped inlet have been found in research to complicate the internal flow field. The strong reverse pressure gradient exists in the large-curvature bending section to finally cause the flow separation phenomenon, and accordingly the total pressure recovery coefficient of the outlet section of the air inlet channel can be reduced, so that the integral effective thrust of the engine is reduced. At the same time, the flow separation phenomenon also causes larger total pressure distortion and secondary rotational flow of the outlet section of the air inlet channel, which can induce the surge of the engine. In order to improve the working range and the working efficiency of the engine and further improve the performance of the fighter plane, it is very necessary to effectively control the separation flow of the S-shaped air inlet channel, and the flow field quality of the outlet of the air inlet channel is improved by a passive or active flow control means.
The most common passive flow control scheme is a vortex generator, which interacts with the boundary layer at a suitable location in the pipeline with a series of fluid structures such as vortices that are spontaneously induced, which will exacerbate the exchange of energy inside the boundary layer, thereby achieving the objective of inhibiting boundary layer separation. However, the control method is simple in structure, but generally only works well under certain working conditions. The structure of the active flow control scheme is relatively more complex, but the active flow control scheme can be actively regulated according to the actual working condition, has good variable working condition performance, and is an ideal and feasible control scheme for a fighter plane with variable operating conditions.
The active flow control method has the advantages that external disturbance and energy injection are required to be introduced, compared with a steady-state blowing/sucking 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 through calculation by using an additional momentum coefficient, and the active flow control method is verified in application research in various fields. These periodic non-steady-state disturbances are generated by a variety of actuators, with synthetic jet actuators, plasma actuators, fluidic oscillators, and the like being typical. However, the aeroengine has severe working conditions, extremely high reliability requirements on all parts, and the difficulty of using unsteady flow control is the 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 periodically oscillating jet at an outlet. The device has the advantages of no movable parts, simple structure, large flow quantity of the outlet, self-oscillation, self-excitation maintenance and the like, and greatly arouses the interest of researchers.
The current test and analysis of jet oscillators are more applied to outflow, however, the application and test scheme of the jet oscillators are still to be further improved for the control problem of the S-shaped air inlet channel internal separation flow. Because of the small outlet size of the fluidic oscillator itself, the area of influence is limited, while the area to be controlled is generally larger in comparison. In order to apply the fluidic oscillators to an actual flow separation control scenario, a series of fluidic oscillator arrays need to be arranged within the flow area being controlled. Thus, a series of discrete periodic oscillating jet excitations are formed at the surface of the controlled area. The internal flow channel of the fluid oscillator is combined with the wall surface design of the air inlet channel, a high-pressure air source is introduced from the outside or in the aeroengine, and the required working frequency and amplitude of the oscillating jet flow are formed at the outlet of the oscillator by adjusting the pressure at the inlet of the flow channel of the fluid oscillator, so that the reduction of the flight resistance of the aircraft and the size of the air inlet channel and the great improvement of the working margin of the engine can be realized on the premise of not increasing the structural complexity of the existing aircraft and not reducing the reliability and safety of the existing aircraft. The S-shaped air inlet flow separation active control technology based on the active excitation of the self-excited oscillation jet flow combines the advantages of high active flow control efficiency and high passive flow control reliability/safety, and achieves good active control effect in a passive control mode. The S-shaped air inlet channel flow loss 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 simultaneously considered, and the S-shaped air inlet channel flow loss control method has a wide prospect in practical engineering application.
The active regulation control effect of the flow in the S-shaped air inlet channel is closely related to the jet flow excitation position, the excitation angle, the distribution position of the exciters, the number of the exciters and the speed and the frequency of exciting jet flow. However, once the design geometry of the fluidic oscillator is determined, the frequency response and speed response of the fluidic oscillator with respect to inlet pressure change are also determined when the working medium characteristics are unchanged. The excitation speed and the excitation frequency can only be adjusted by adjusting the inlet pressure. In order to quantitatively study the influence of the different excitation parameters on the flow quality of the S-shaped air inlet channel/flow channel, a great deal of parametric experimental study is needed, wherein the influence comprises the influence of jet excitation positions, excitation angles, the number of exciters and the distribution positions of the exciters besides the excitation speed and the frequency. The combination of each group of parameters requires the processing of complex flow passages of a plurality of fluid oscillators on the wall surface of the S-shaped air inlet channel, which results in excessive test cost and overlong 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, which can meet the requirements of various design parameters and processing precision through modularized design, improves convenience and ensures the accuracy of a test.
The technical scheme adopted by the invention is as follows:
An S-channel flow control variable parameter test system comprising:
The curved section of the tube is provided with a curved portion,
The replaceable plugboard is arranged on the bending section and can be detachably arranged on the bending section;
A mounting groove is formed in the replaceable plugboard at the position to be tested;
a replaceable fluid oscillator mounted in the mounting groove, wherein the replaceable fluid oscillator is detachably connected with the mounting groove, and a jet outlet of the replaceable fluid oscillator faces to an inner flow passage of the bending section;
And the straight sections are arranged at two ends of the bending section and are in smooth connection with the inside of the bending section.
Further, the replaceable plugboards at each position on the bending section are provided with a plurality of parts, one part of the replaceable plugboards is not provided with mounting grooves, and the other part of the replaceable plugboards is provided with mounting grooves at different positions.
Further, a single position to be tested, or a plurality of test positions, is provided at the curved section.
Further, the replaceable fluid oscillator comprises a connecting part and an upper convex part at the upper part of the connecting part, wherein the upper convex part is a convex block with a slope, and a jet outlet of an oscillator array in the replaceable fluid oscillator is arranged on the upper surface of the upper convex part.
Furthermore, the mounting groove is a slope groove matched with the upper convex part, the upper convex part is buckled and connected with the mounting groove, and the connecting part is detachably connected with the replaceable plugboard through a connecting piece.
Furthermore, the adjacent replaceable plugboards and the adjacent straight sections are designed to be mutually matched in a step shape, and the replaceable plugboards and the adjacent straight sections are detachably connected by using the connecting piece.
Further, an oscillator array is arranged in the replaceable fluid oscillator, the included angle between the jet flow injection direction of the oscillator array and the internal flow channel is alpha, and the value range of alpha is 15-90 degrees.
Further, the jet outlet 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, wherein the oscillator mounting side 7 is provided with an oscillator array, and the oscillator mounting side is fixedly connected with the cover plate.
Further, the replaceable fluid oscillator is formed by CNC precision machining, integrated 3D printing, or other forming modes.
Advantageous effects
1. The S-shaped flow channel flow control variable parameter testing system provided by the invention adopts a double replaceable structure of the replaceable plugboard and the replaceable fluid oscillator array, wherein the excitation position of the oscillator can be changed by changing the position of the buckling groove on the replaceable plugboard, so that the influence of the active excitation position on the control effect is studied. The influence of different excitation position parameters on active control can be studied on the premise of not changing the original S-shaped flow channel structure and the structure of the oscillator array only by replacing the plugboard and only by ensuring the shape part of the buckling groove. The multi-variable research is realized, the cost of parameter research is saved, and the economy and experimental efficiency are improved.
On the same replaceable plugboard, the influence rules of different excitation parameters on the flow control efficiency are studied by changing the number of the fluid oscillators on different arrays, namely, changing the size of the fluid oscillators, the distribution interval of the oscillators, the type of the oscillators, different jet excitation angles and the like.
2. The replaceable plugboard is connected with the S-shaped runner in a stepped buckling mode, and the buckling surface is connected and sealed by adopting a sealing ring and a fastening bolt, so that gas leakage caused by machining errors and installation accuracy is avoided.
3. The exciter array is buckled and connected with the plugboard through the buckling groove with the slope, the slope structure can realize the rapid buckling of the exciter array, and the installation of the large-angle oscillator in a small volume is guaranteed. The design of the buckling surface of the oscillator array and 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 disassembled and assembled, and meanwhile, the mounting gap is reduced, and gas leakage is avoided.
4. In order to study the influence of the included angle between the jet direction of the oscillator and the incoming flow direction, fluid oscillator arrays with different inclination angles are required to be manufactured, and in the application, the replaceable fluid oscillators with different jet types and different jet angles are consistent with the assembly surface of the mounting groove on the plugboard, so that the outlet jet positions of the arrays with different angles are consistent.
5. The test system can meet the requirements of various design parameters and machining precision through modularized design, and ensures the accuracy of the test per se while improving convenience.
6. The exciter is symmetrically fastened and sealed through the countersunk head bolts, so that the exciter control test of various angles can be realized, the influence of machining errors and the influence of machining defects on results are reduced, meanwhile, specific requirements on test section materials are not required any more, and metal machining or 3D printing parts can achieve ideal effects.
Drawings
FIG. 1 is a schematic diagram of an S-type flow channel flow control variable parameter test system according to the present invention;
FIG. 2 is a schematic diagram of a replaceable insert;
FIG. 3 is a schematic diagram of a replaceable actuator configuration;
FIG. 4 is a schematic view of the assembly of the replaceable actuator, replaceable insert, and S-shaped flow channel walls;
FIG. 5 is a schematic diagram of a replaceable actuator configuration;
FIG. 6 is a schematic view of a 45 degree angle replaceable actuator;
FIG. 7 is a schematic view of a 90 degree angle replaceable actuator;
FIG. 8 is a superimposed state diagram of a 45 angle replaceable actuator configuration and a 90 angle replaceable actuator;
FIG. 9 is a schematic diagram of an assembly of a replaceable actuator with a replaceable insert;
FIG. 10 is a schematic diagram of an oscillator array within a replaceable actuator;
FIG. 11 is a schematic diagram of four different configurations of a fluidic oscillator array, (a) relaxation oscillator, (b) sonic oscillator, (c) Conda sweep oscillator, and (d) jet coupled oscillator;
FIG. 12 is a schematic view of a replaceable fluidic oscillator from the outside and from the inside;
In the figure, 1, a bending section, 2, an inlet straight section, 3, an outlet straight section, 4, a replaceable plugboard, 4a, a first replaceable plugboard, 4b, a second replaceable plugboard, 5, a mounting groove, 6, a replaceable fluid oscillator, 6-1, an upper convex part, 6-2, a connecting part, 6-3 lower convex parts, 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 countersink.
Detailed Description
The present invention will be described in further detail with reference to the drawings and examples, in order to make the objects, technical solutions and advantages of the present invention more apparent. It should be understood that the specific embodiments described herein are for purposes of illustration only and are not intended to limit the scope of the invention.
Aiming at the defects existing in the prior art, the application designs an S-shaped runner flow control variable parameter testing system 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 passage is rectangular, but the shape is not limited to this, and may be various shapes such as a circular shape.
In this embodiment, an S-shaped flow channel with a rectangular cross section is further described:
The straight section comprises an inlet straight section 2 and an outlet straight section 3, flanges are respectively arranged at the outermost sides of the inlet straight section 2 and the outlet straight section 3, the inlet straight section 2 is used for supplying incoming flow through a flange wind tunnel, the incoming flow conditions required by the experiment are provided for the S-shaped runner flow control experiment, and the outlet straight section 3 is respectively connected with an output pipeline through the flanges.
The inlet straight section 2 and the outlet straight section 3 are respectively arranged at two sides of the bending section 1, and the bending 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 a flow structure such as flow separation, flow direction vortex and the like.
More specifically, the curved section 1 may be made of various materials such as metal, plexiglas, etc., and may be machined by various means such as machining, laser cutting, etc.
The bending section 1 is an S-shaped runner formed by smoothly connecting a plurality of replaceable plugboards 4. As seen from fig. 1, the replaceable insert plates 4 on the upper and lower parts of the bending section 1 are curved, and like the two replaceable insert plates 4 on the upper part are reversely bent, so that an S-shaped channel is formed after the two replaceable insert plates 4 on the lower part are connected, the two replaceable insert plates 4 on the upper part are designed in the same way, and the S-shaped channels formed by connecting the upper and lower parts are parallel to each other. A smooth connection between the two interchangeable insert plates 4 connected to each other in the flow direction is required to ensure that the flow channel interior is smooth. The side wall interchangeable insert board 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 because factors influencing the active regulation control effect are closely related to the position and the angle of jet flow excitation, the distribution positions of the exciters, the number of the exciters and the speed and the frequency of exciting jet flow. In order to be able to carry out the change of the parameters and the quantitative investigation in the same test system, the application therefore provides for the interchangeable insert board 4 to be designed in the bending section 1. With reference to fig. 4, the adjacent replaceable plugboards 4, the replaceable plugboards 4 and the adjacent straight sections are all designed to be mutually matched in a step shape, and the replaceable plugboards 4 can be detachably mounted from the outside by using connecting pieces such as screws while being rapidly positioned by utilizing the mutually matched step-shaped structures. In fig. 4, the connection parts between the left end of the replaceable plugboard 4 and the inlet straight section 2 are all in a ladder shape, and are mutually matched and then locked by screws from the outside, so that the replaceable plugboard 4 can be directly disassembled when the replaceable plugboard 4 needs to be replaced. The connection part between the right end of the replaceable plugboard 4 and the other replaceable plugboard 4 is designed to be stepped, and the replaceable plugboard and the other replaceable plugboard are matched with each other and then locked by screws from the outside. The advantage of the screw locking from the outside is that the installation is convenient, and the screw can not extend to the internal flow channel simultaneously, has guaranteed the smoothness of internal flow channel.
The application is provided with the mounting groove 5 on the replaceable plugboard 4, the replaceable fluid oscillator 6 is arranged on the mounting groove 5, and the jet outlet 6-4 of the replaceable fluid oscillator 6 is arranged towards the inside of the flow channel. In order to enable the replaceable fluid oscillator 6 to be replaced, the replaceable fluid oscillator 6 is detachably arranged in the mounting groove 5, so that the replaceable fluid oscillator 6 with different jet types and different jet angles can be replaced.
More specifically, in order to be able to change the test position of the exchangeable fluidic oscillator 6, the exchangeable insert plate 4 at each position on the curved section 1 is provided with a plurality of exchangeable insert plates, one part of the exchangeable insert plate 4 is not provided with the mounting groove 5, and the other part of the exchangeable insert plate 4 is provided with the mounting groove 5 at a different position. When the test position needs to be changed, only one replaceable insert 4 with a different mounting slot 5 position needs to be replaced. For example, in fig. 1, the uppermost part of the first replaceable insert 4a of the upper part is provided with a mounting groove 5, and when other positions of the first replaceable insert 4a need to be tested, only the first replaceable insert 4a provided with the mounting groove 5 at another different position needs to be replaced, so that the testing position of the replaceable fluid oscillator 6 is changed, and other positions are the same. The application can realize the adjustment of the test position, jet type and jet angle by replacing the replaceable plugboard and the replaceable fluid oscillator 6, the whole structure of the test system is unchanged, and the test system is not required to be designed for each change, so that the test cost can be reduced, and the test period can be shortened by carrying out multiple tests by quick replacement.
More specifically, the system can also test a plurality of positions at the same time, for example, in fig. 1, the first replaceable insert 4a at the upper part and the second replaceable insert 4b at the lower part can be replaced by a mounting groove 5, and the replaceable fluid oscillator 6 is arranged in the mounting groove 5, so that the test can be performed at the first replaceable insert 4a and the second replaceable insert 4b at the lower part at the same time.
More specifically, when the replaceable fluid oscillators 6 of different jet types and different jet angles are required to be tested at the same test position, the replaceable fluid oscillators 6 of different jet types and different jet angles are required to be replaced, but the positions of the jet outlets 6-4 of the replaceable fluid oscillators 6 before and after replacement are required to be ensured to be the same. The present application is achieved by optimizing the structure of the replaceable fluid oscillator 6 and the mounting groove 5 against this problem. Referring to fig. 2 and 3, the mounting groove 5 is a groove with a slope, the cross section of the mounting groove 5 is trapezoid, the connecting part of the replaceable fluid oscillator 6 and the mounting groove 5 is an upper convex part 6-1, the upper convex part 6-1 is a cube with a slope, and the rapid positioning between the two parts can be realized through the matching of the slope surface of the upper convex part 6-1 and the slope surface of the mounting groove 5. At the same time, the jet outlets 6-4 of the replaceable fluid oscillators 6 of different jet types and different jet angles are positioned at the same time, and as shown in FIG. 9, the distances from the center line of the jet outlets 6-4 of all the replaceable fluid oscillators 6 to the rear edge (divided into a front edge and a rear edge in the flowing direction) of the mounting groove 5 are the same.
More specifically, the replaceable fluid oscillator 6 is detachably connected to the first replaceable insert 4a where the mounting groove 5 is located. As shown in fig. 5, the replaceable fluid oscillator 6 includes a connection portion 6-2, and an upper protruding portion 6-1 on an upper portion of the connection portion 6-2, and the connection portion 6-2 is detachably connected to the replaceable insert plate 4 by a connection member such as a screw. Inside the lower protruding part 6-3 is an oscillator array.
More specifically, the replaceable fluid oscillator 6 is a double-layer assembly type, and the replaceable fluid 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 is fixedly connected with the cover plate 8.
More specifically, the replaceable fluid oscillator 6 may be CNC precision machined, integrated 3D printed, or otherwise formed.
More specifically, the oscillator array may employ a relaxation type oscillator, a sonic type oscillator, a coanda sweep type oscillator, or a jet coupling type oscillator as shown in fig. 11. The structural size and arrangement pitch of the oscillator array are more scalable under this design. The oscillator array requiring precision machining can be performed in various manners such as metal machining, 3D printing and the like. Compared with the traditional experimental scheme, the volume of the precision machining structure is reduced, the defect of insufficient machining precision of a large structural part is avoided, and the precision of the channel structure matching experiment with lower machining precision is ensured.
More specifically, the jet angle of the oscillator array is that the jet direction of the oscillator array has an included angle alpha with the incoming flow direction, and the alpha can be changed between 15 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 ° inclination array, fig. 7 shows a 90 ° inclination array, and the positions of the jet outlets 6-4 of the replaceable fluid oscillators 6 showing different jet angles are the same, and in combination with fig. 8, the two replaceable fluid oscillators 6 of fig. 6 and 7 are shown to be overlapped, and it can be seen that the upper convex portions 6-1 of the two replaceable fluid oscillators 6 are completely overlapped.
More specifically, for the installation of the replaceable fluidic oscillator 6, the structure of the replaceable fluidic oscillator 6 may be different according to the installation position of the replaceable fluidic oscillator 6 in the actual assembly process, and for the connection between the replaceable fluidic oscillator 6 and the replaceable insert plate 4, different connection modes may be adopted, and according to the installation direction of the connection piece between the replaceable fluidic oscillator 6 and the replaceable insert plate 4, two modes may be divided into a fixed connection from the outside and a fixed connection from the inside.
For the two replaceable fluid oscillators 6 shown in fig. 6 and 7, if the width of the connecting part 6-2 of the replaceable fluid oscillator 6 is enough and the connecting part 6-2 can be well attached to the replaceable plugboard 4 where the replaceable fluid oscillator is to be installed, as shown in the area A of fig. 12, for the connection of the replaceable fluid oscillator 6 and the replaceable plugboard 4 in the area A through connecting pieces such as bolts, the bolts are connected from the outside of the whole flow channel to the inside of the flow channel, the bolts sequentially pass through the outer connecting holes 6-5 on the connecting part 6-2 and the connecting holes on the replaceable plugboard 4 to realize the connection of the two, a plurality of the outer connecting holes 6-5 are uniformly arranged on the connecting part 6-2 and are also installed from the outside and the inside through bolts, and at the moment, the connecting holes on the replaceable plugboard 4 corresponding to the outer connecting holes 6-5 are blind holes, namely the bolts cannot extend into the flow channel, so that the smoothness of the flow channel can be ensured.
However, for the installation of the fastening piece with insufficient width of the connecting portion 6-2, and the arc is formed between the connecting portion 6-2 and the replaceable insert plate 4 to be installed, the connecting portion 6-2 cannot be well attached to the area B in fig. 12 (or the installation condition of the connecting portion 6-2 at the left side in fig. 6 from outside to inside of the fastening piece), in this case, if the connecting manner from outside to inside is adopted in the area B as in the area a, the connecting piece cannot be uniformly distributed around the connecting portion 6-2 in the area B, and the asymmetric bolt fastening easily causes gaps and local deformation, and the gaps and the local deformation can cause various problems such as gas leakage, flow field distortion and the like, which affect the experimental result. In order to solve the problem, the invention adopts the connecting piece to be installed from the inside of the flow channel to the outside of the flow channel for the region B. The surface of the replaceable plugboard 4 in the flow channel in the area B is provided with a plurality of countersunk holes 10 as shown in fig. 9, the countersunk holes 10 are uniformly arranged along the side edge of the jet outlet 6-4, a plurality of inner connecting holes 6-6 are uniformly arranged on the connecting part 6-2, the inner connecting holes 6-6 are in one-to-one correspondence with the countersunk holes 10, and when the replaceable plugboard is installed, a connecting piece such as a bolt is inserted into the inner connecting holes 6-6 corresponding to the countersunk holes 10 from the countersunk holes 10, so that the replaceable plugboard 4 and the replaceable fluid oscillator 6 are connected. Since the countersunk holes 10 are formed on the surface of the replaceable insert plate 4 in the runner, the countersunk holes 10 damage the smoothness of the runner, and in order to ensure the smoothness of the runner in the region B, after the bolts are installed, materials such as gypsum are used as fillers to fill up the countersunk holes 10.
In addition, the inner connecting hole 6-6 and the outer connecting hole 6-5 formed on the same side of the connecting portion 6-2 need to be staggered by a certain distance, and cannot overlap, as shown in the left side of fig. 3, fig. 3 only shows the illustration of the inner connecting hole 6-6 and the outer connecting hole 6-5 on the left connecting portion 6-2, and in actual use, the inner connecting hole 6-6 and the outer connecting hole 6-5 on the right connecting portion 6-2 may be disposed as such.
The connection mode of the replaceable fluid oscillator 6 and the replaceable plugboard 4 can well balance the stress on two sides of the oscillator array, avoid warping, gaps and local deformation, and further ensure the characteristic of main flow. After the fastening bolt is arranged on one side of the main runner, the bolt hole is filled with fillers such as sealant, so that the flow field can be prevented from being influenced by local gaps and deformation.
The above embodiments are merely for illustrating the design concept and features of the present invention, and are intended to enable those skilled in the art to understand the content of the present invention and implement the same, the scope of the present invention is not limited to the above embodiments. Therefore, all equivalent changes or modifications according to the principles and design ideas of the present invention are within the scope of the present invention.
Claims (9)
1. An S-shaped flow channel flow control variable parameter test system, comprising:
A curved section (1),
The replaceable plugboard (4) is arranged on the bending section (1), and the replaceable plugboard (4) is detachably arranged on the bending section (1);
A mounting groove (5) is arranged on the replaceable plugboard (4) at the position to be tested;
A replaceable fluid oscillator (6) mounted in the mounting groove (5), wherein the replaceable fluid oscillator (6) is detachably connected with the mounting groove (5), and a jet outlet of the replaceable fluid oscillator (6) faces to an inner flow channel of the bending section (1);
The straight sections are arranged at two ends of the bending section (1) and are smoothly connected with the inside of the bending section (1);
The replaceable plugboards (4) at each position on the bending section (1) are provided with a plurality of parts, one part of the replaceable plugboards (4) is not provided with a mounting groove (5), the other part of the replaceable plugboards (4) is provided with a mounting groove (5) at different positions,
A single position to be tested, or a plurality of test positions, is provided at the curved section (1).
2. An S-channel flow control variable parameter test system according to claim 1, wherein the replaceable fluid oscillator (6) comprises a connecting portion (6-2), and an upper protruding portion (6-1) at an upper portion of the connecting portion (6-2), the upper protruding portion (6-1) being a protruding portion with a slope;
Jet outlets (6-4) of the oscillator array in the replaceable fluid oscillator (6) are arranged on the upper surface of the upper convex part (6-1).
3. The S-shaped runner flow control variable parameter testing system according to claim 2, wherein the mounting groove (5) is a sloping groove matched with the upper convex part (6-1), and the upper convex part (6-1) is buckled and connected with the mounting groove (5);
The connecting part (6-2) is detachably connected with the replaceable plugboard (4) through a connecting piece.
4. An S-channel flow control variable parameter testing system according to claim 2, wherein the steps between adjacent replaceable insert plates (4) and between the replaceable insert plates (4) and the adjacent flat sections are designed to be mutually matched, and the connectors are used for detachable connection.
5. An S-channel flow control variable parameter testing system according to claim 2, wherein the replaceable fluid oscillator (6) is internally provided with an oscillator array, and the included angle between the jet injection direction of the oscillator array and the internal channel is alpha, and the value of alpha is in the range of 15-90 degrees.
6. An S-channel flow control variable parameter test system according to claim 2 or 5, wherein the jet outlets (6-4) of the oscillator arrays of different jet angles are located at the same position.
7. The system of claim 5, wherein the oscillator array is a relaxation-type oscillator, a sonic-type oscillator, a coanda sweep-type oscillator, or a jet-coupled-type oscillator.
8. An S-channel flow control variable parameter testing system according to claim 5, characterized in that said exchangeable 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 oscillator array, and the oscillator mounting side (7) is fixedly connected with the cover plate (8).
9. The S-channel flow control variable parameter testing system according to claim 7, wherein the replaceable fluid oscillator (6) is formed by CNC precision machining, integral 3D printing, or other forming methods.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210440712.XA CN114791348B (en) | 2022-04-25 | 2022-04-25 | S-shaped runner flow control variable parameter test system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210440712.XA CN114791348B (en) | 2022-04-25 | 2022-04-25 | S-shaped runner flow control variable parameter test system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114791348A CN114791348A (en) | 2022-07-26 |
| CN114791348B true CN114791348B (en) | 2025-08-12 |
Family
ID=82461165
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210440712.XA Active CN114791348B (en) | 2022-04-25 | 2022-04-25 | S-shaped runner flow control variable parameter test system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114791348B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115750132A (en) * | 2022-11-16 | 2023-03-07 | 西北工业大学 | Equivalent spray pipe structure for simulating performance of S-shaped spray pipe |
| CN119178574B (en) * | 2024-11-22 | 2025-01-28 | 中国空气动力研究与发展中心低速空气动力研究所 | Coanda jet flow test device for optical measurement |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN217276794U (en) * | 2022-04-25 | 2022-08-23 | 中国航空发动机研究院 | S-shaped flow channel flow control variable parameter testing system |
Family Cites Families (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20090261206A1 (en) * | 2005-01-21 | 2009-10-22 | Alvi Farrukh S | Method of using microjet actuators for the control of flow separation and distortion |
| CN102230848A (en) * | 2007-12-03 | 2011-11-02 | 哈尔滨工业大学 | Method for acquiring optimal classification surface of hypersonic speed air inlet starting/non-starting mode |
| WO2010046704A2 (en) * | 2008-10-23 | 2010-04-29 | Mbda Uk Limited | Improvements in and relating to air-breathing flight vehicles |
| CZ2011477A3 (en) * | 2011-08-05 | 2013-04-24 | Ústav termomechaniky AV CR, v.v.i. | Fluidic oscillator with bistable jet-type amplifier |
| CN211692653U (en) * | 2020-01-09 | 2020-10-16 | 厦门大学 | An S-shaped air intake |
| CN111521365B (en) * | 2020-05-18 | 2021-06-08 | 南京航空航天大学 | Adjustable frequency and phase unsteady flow control experimental device based on rotary slot grating |
| CN111810295B (en) * | 2020-07-17 | 2022-03-04 | 中国航空发动机研究院 | Flow separation active control structure, method and application |
| CN113074047A (en) * | 2021-03-04 | 2021-07-06 | 南京航空航天大学 | S-shaped air inlet channel rotational flow distortion flow control device based on fluid oscillator |
| CN113389492B (en) * | 2021-05-08 | 2022-06-03 | 德州联合石油科技股份有限公司 | Controllable hydraulic oscillator |
| CN114370337B (en) * | 2022-01-14 | 2023-05-23 | 中国航空发动机研究院 | Jet oscillator |
-
2022
- 2022-04-25 CN CN202210440712.XA patent/CN114791348B/en active Active
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN217276794U (en) * | 2022-04-25 | 2022-08-23 | 中国航空发动机研究院 | S-shaped flow channel flow control variable parameter testing system |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114791348A (en) | 2022-07-26 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN114791348B (en) | S-shaped runner flow control variable parameter test system | |
| Woszidlo et al. | Parametric study of sweeping jet actuators for separation control | |
| US8382043B1 (en) | Method and apparatus for aerodynamic flow control using compact high-frequency fluidic actuator arrays | |
| Koklu et al. | Comparison of sweeping jet actuators with different flow-control techniques for flow-separation control | |
| US7018172B2 (en) | Airfoil surface impedance modification for noise reduction in turbofan engines | |
| Hamstra et al. | Active inlet flow control technology demonstration | |
| EP3770067B1 (en) | Leading-edge thermal anti-ice systems and methods | |
| US10518605B2 (en) | Aircraft turbomachine comprising a deflector | |
| CN111810295B (en) | Flow separation active control structure, method and application | |
| Otto et al. | Comparison of various fluidic oscillators for separation control on a wall-mounted hump | |
| Bauer et al. | Experiments on active drag reduction on a complex outer wing model | |
| CN217276794U (en) | S-shaped flow channel flow control variable parameter testing system | |
| KOBAYASHI et al. | Jet vectoring using secondary Coanda synthetic jets | |
| US11162370B2 (en) | Actively cooled component | |
| US9267463B2 (en) | Gas turbine engine systems involving variable nozzles with flexible panels | |
| CN115465445B (en) | A rudderless airfoil lift device based on non-feedback oscillating jet | |
| Schloesser et al. | Fluidic actuators for separation control at the engine/wing junction | |
| Osmokrovic et al. | Laminar boundary-layer response to spanwise periodic forcing by dielectric-barrier-discharge plasma-actuator arrays | |
| CN114562472B (en) | Compressor test structure | |
| Staats et al. | Experimental investigations on active flow control applied to an asymmetric compressor cascade | |
| Zhang et al. | Experimental study on aerodynamic properties of circulation control airfoil with plasma jet | |
| Jeyalingam | Towards the noise reduction of synthetic jet actuators using lobed orifices | |
| CN120333845B (en) | Gas engine turbine blade test piece structure with easily replaceable cooling elements and adjustable cooling air | |
| Siller et al. | Jet-noise investigations in a small scale facility | |
| Schloesser et al. | Optimization and Testing of Fluidic Actuators for Active Flow Control At the Engine/Wing Junction |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |