Experimental Device for Parametric Study on Noise Reduction of Annular Compressor Wave Leading Edge Blades

Abstract

The present invention provides an experimental device for parametric research on noise reduction of a ring compressor with a wavy leading-edge vane cascade, including a turbulence generation component, a ring compressor vane cascade experimental component, and an acoustic mode measurement component, all of which are in the shape of a rotating body. The turbulence generation component is docked with a blowing wind tunnel. The hub of the ring compressor vane cascade experimental component is fixedly connected to the hub of the acoustic mode measurement component. The casing of the ring compressor vane cascade experimental component is connected to the acoustic wave stabilizer in the acoustic mode measurement component. The hub of the acoustic mode measurement component is located inside the acoustic wave stabilizer and the casing of the acoustic mode measurement component. The motor drives the turbulence generation component to rotate, and different intensities of oncoming flow turbulence are generated by different specifications of flow-around round rods installed thereon. Different specifications of blades are installed between the hub and the casing of the ring compressor vane cascade experimental component, so as to quantitatively analyze and study the noise reduction effects of different specifications of bionic blades from the perspective of the acoustic mode of the ring duct, and carry out parametric acoustic experiments on bionic blades.

Description

Technical Field

[0001] The present invention relates to the field of pneumatic-acoustic experiments of annular pipelines, and is mainly applicable to the application research of low-noise blades. Specifically, it is an experimental device for an annular compressor cascade and an outlet acoustic measurement device. Background Art

[0002] For turbomachinery such as aeroengines, compressors, and ventilators, its noise is mainly composed of two parts: rotor / stator interference tonal noise and turbulent broadband noise. Among them, the rotor / stator interference tonal noise is generated by the interference between the rotating wake of the rotor and the downstream stator blades, and the turbulent broadband noise is generated by the interference of various turbulences (boundary layer turbulence, wake turbulence, etc.) and solid surfaces. The most important part of the turbulent broadband noise is the rotor / stator interference broadband noise. Therefore, the current research focus is on the rotor / stator interference tonal noise and the rotor / stator interference broadband noise.

[0003] With the development of the times and people's yearning for a better life, the noise problem has become increasingly prominent, causing serious impacts on the lives and work of residents around airports and factory workers. Therefore, it is urgent to reduce the noise problem of turbomachinery. Although with the development of computers, it has been possible to relatively accurately evaluate the noise level using computational fluid dynamics and computational aeroacoustics, and the noise reduction mechanism can be studied in depth. However, there are still great limitations in using computer technology to study aerodynamic noise. For example: 1. It is still mainly applied to two-dimensional or simple three-dimensional models; 2. The theoretical model is simplified and cannot match the complex situations in real turbomachinery; 3. The computational cost required for calculation is very large, and it is impossible to complete the parametric study of a large number of samples.

[0004] Therefore, using experimental means to conduct noise reduction experiments is still the most effective method. Relevant scholars have concluded through a large number of experimental and numerical studies that for turbomachinery, its main noise sources are the dipole noise sources on the blade surface and the quadrupole noise sources generated by the surrounding turbulence. Over the years, in order to reduce noise, scholars have mainly carried out research from two aspects: 1. Reducing the amplitude of sound waves and changing their phase from the noise propagation path; 2. Reducing the intensity of noise sources from the source. The research in the first aspect has been very in-depth, but due to the limitations of the engine weight and size, the installation position of the acoustic lining is limited, making it difficult to make further progress and application in this aspect. The research in the second aspect is directly related to aerodynamic performance and acoustic performance, with great advantages and development space. Especially in recent years, the development of bionic blades has pushed the research in this aspect to a new height. However, due to reasons such as experimental costs and assembly difficulties, it is not practical to directly apply the designed bionic blades to real turbomachinery; and the annular cascade effect and annular duct acoustic effect cannot be considered through isolated blade blowing experiments and planar cascade experiments. In order to conduct a large number of experiments, obtain a large number of experimental results for parametric analysis and research, and at the same time ensure the duct effect, it is necessary to carry out parametric research on bionic blades using an annular cascade. At present, in the research of cascade acoustics, there is no public information on studying the aerodynamic performance and acoustic performance of bionic blades through an annular cascade. Summary of the Invention

[0005] The technical problem to be solved by the present invention is: To solve the limitations of existing experimental devices for studying the aerodynamic performance and acoustic performance of bionic blades, the present invention provides an experimental device for parametric research on noise reduction of the wave leading edge cascade of an annular compressor.

[0006] In order to achieve the above-mentioned invention purpose, the technical solution adopted by the present invention is: An experimental device for parametric research on noise reduction of the wave leading edge cascade of an annular compressor, including a motor. It is characterized in that it further includes a rotating turbulence generation component 1, an annular compressor cascade experimental component 2, and an acoustic mode measurement component 3, all of which are in a rotary body shape; the motor is fixed inside the annular compressor cascade experimental component 2 and the acoustic mode measurement component 3, and the motor shaft is fixedly connected to the rotating turbulence generation component 1 to drive the rotating turbulence generation component 1 to rotate; one end of the rotating turbulence generation component 1 is connected to the blowing wind tunnel, and the other end is coaxially butted with the air inlet of the annular compressor cascade experimental component 2; the air outlet of the annular compressor cascade experimental component 2 is fixedly connected to the air inlet of the acoustic mode measurement component 3 in a coaxial manner;

[0007] The annular compressor cascade experimental assembly 2 includes a cascade experimental hub 4, a cascade experimental casing 5, a cascade experimental cascade 6 and a cascade cover plate 7; a plurality of blade mounting grooves are radially formed on the side walls of the cascade experimental hub 4 and the cascade experimental casing 5, both ends of the experimental cascade 6 are respectively embedded in the blade mounting grooves, and the cascade cover plate 7 is installed in the blade mounting grooves on the cascade experimental casing and fixes the experimental cascade 6 to ensure stable installation and airtightness;

[0008] The acoustic mode measurement assembly 3 includes an acoustic wave stabilizer 8, an acoustic mode measurement casing 9 and an acoustic mode measurement hub 10, all of which are in the shape of a rotating body with an internal cavity. The acoustic mode measurement hub 10 is located inside the acoustic wave stabilizer 8 and the acoustic mode measurement casing 9 and is coaxially and fixedly connected to the cascade experimental hub 4. Both ends of the acoustic wave stabilizer 8 are coaxially and fixedly connected to the cascade experimental casing 5 and the acoustic mode measurement casing 9 respectively. A plurality of microphones are radially installed on the side wall of the acoustic mode measurement casing 9.

[0009] It further includes a flow-around round bar 11; a plurality of mounting holes with different specifications are radially arranged on the side wall of the rotating turbulent flow generating assembly 1, and the flow-around round bar 11 is installed in the mounting holes. Different specifications of flow-around round bars can generate Karman vortex streets with different frequencies and oncoming flow turbulences with different intensities, so as to truly simulate the rotation / stator interference process of a fan / compressor.

[0010] Furthermore, the experimental cascade 6 includes biomimetic blades. The biomimetic blades include a biomimetic blade leading edge 13 and a biomimetic blade trailing edge 14. One side of the biomimetic blade leading edge 13 is wavy, and the other side is provided with a wedge-shaped convex block. One side of the biomimetic blade trailing edge 14 is provided with a wedge-shaped groove matching the wedge-shaped convex block on the biomimetic blade leading edge; mounting holes are arranged along the length direction of the wedge-shaped groove on the end face of the biomimetic blade trailing edge 14 for fixedly connecting the blade to the cascade cover plate 7 to ensure the airtightness of the blade.

[0011] Furthermore, the biomimetic blade leading edge 13 of the biomimetic blade is made by 3D printing.

[0012] Furthermore, the blade mounting grooves include a plurality of square grooves and strip grooves. The inner walls of the square grooves and the strip grooves are matched with the arc surface of the side wall of the experimental cascade. The square grooves and the strip grooves are arranged at intervals.

[0013] Furthermore, to ensure uniform exhaust, the acoustic mode measurement hub 10 extends out of the cavity of the acoustic mode measurement casing 9, and the extending end is hemispherical.

[0014] Furthermore, it further includes a filling block, which is installed in the blade mounting grooves on the cascade experimental section hub 4 to ensure stable blade mounting and airtight airflow when the cascade experimental hub 4 and the experimental cascade 6 are installed.

[0015] Invention effects

[0016] 1. In the present invention, the blades in the experimental cascade adopt a two-section structure form, including a blade leading edge and a blade trailing edge. The two sections are detachably connected into one body through the cooperation of a wedge block and a wedge groove, which is convenient for adjusting and replacing the number of blades during the experiment, ensuring the requirements of the parametric experiment of the bionic blade in the annular duct, and facilitating the exploration experiment research on the influence of blade pitch on the acoustic performance.

[0017] 2. The cost of the existing integral blade is about 30,000 yuan. The present invention uses two-section processing for the blades, and about 30 blades cost about 0.3 ten thousand yuan. Since it is generally necessary to conduct experimental research on a large number of blade configurations, assuming that a total of 5 groups of blades need to be experimentally studied, the existing integral processing cost is 150,000 yuan, while the blade processing cost of the present invention only needs 60,000 yuan. The processing cost is reduced and the economic applicability is strong.

[0018] 3. In the present invention, a plurality of blade mounting grooves are opened on the side walls of the cascade experimental hub 4 and the cascade experimental casing 5. The two ends of the blade are respectively embedded in the blade mounting grooves and fixed by the cascade cover plate, ensuring the installation stability and airtightness of the blade.

[0019] 4. In the present invention, a sound-absorbing lining can be installed between the turbulence generating component and the blowing wind tunnel to reduce the influence of the noise generated by the blowing wind tunnel on the measurement results. Before starting the formal experiment, it is necessary to measure the atmospheric parameters and air flow velocity of the blowing wind tunnel air flow to ensure the accuracy and reliability of the experiment.

[0020] 5. In the present invention, a plurality of flow-around round rods with different specifications are radially installed on the side wall of the turbulence generating component. The flow-around round rods with different diameters can, on the one hand, generate Karman vortex streets with different frequencies, and on the other hand, generate oncoming flow turbulence with different intensities, so as to truly simulate the rotor / stator interference process of the fan / compressor.

[0021] 6. The present invention can synchronously complete the signal acquisition of the sound field in the pipeline through the sound mode measurement component, accurately complete the sound field reconstruction, and accurately evaluate the noise reduction effect of various specifications of bionic blades, improving the applicable range of the bionic blade acoustic experiment, facilitating the more in-depth development of the parametric acoustic experiment of the bionic blade from the aspect of the real annular pipeline acoustics, and being conducive to guiding the parametric design of the bionic blade. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 is the overall structure diagram of the device of the present invention

[0023] Figure 2 is the structural diagram of the annular compressor cascade experimental component in the device of the present invention;

[0024] Figure 3 is the structural diagram of the sound mode measurement component in the device of the present invention;

[0025] Figure 4Schematic diagram of flow around a circular rod and motor installation;

[0026] Figure 5 For Figure 2 Structural diagram of the middle vane cover plate;

[0027] Figure 6 Schematic diagram of the leading edge of the reference blade in the present invention;

[0028] Figure 7 Schematic diagram of the leading edge of the bionic blade in the device of the present invention;

[0029] Figure 8 Schematic diagram of the trailing edge of the bionic blade in the device of the present invention;

[0030] Figure 9 Schematic diagram of the modal maximum cut-off range of the annular cascade in the embodiment;

[0031] Figure 10 Schematic diagram of the acoustic field evaluation result of the annular cascade in the embodiment.

[0032] In the figure, 1 - rotating turbulence generation component, 2 - annular compressor vane cascade experimental component, 3 - acoustic mode measurement component, 4 - vane cascade experimental hub, 5 - vane cascade experimental casing, 6 - experimental vane cascade, 7 - vane cascade cover plate, 8 - acoustic wave stabilizer, 9 - acoustic mode measurement casing, 10 - acoustic mode measurement hub, 11 - flow-around circular rod, 12 - motor, 13 - leading edge of the bionic blade, 14 - trailing edge of the bionic blade. Detailed implementation manners

[0033] For turbomachinery, its main noise sources are the dipole noise sources on the blade surface and the quadrupole noise sources generated by the surrounding turbulence. To address the problem of reducing the noise of turbomachinery, existing technologies conduct research through bionic cascade experiments. However, due to reasons such as high experimental costs and difficult assembly, bionic blades cannot be directly applied to real turbomachinery. Moreover, through existing isolated blade blowing experiments and planar cascade experiments, the annular cascade effect and annular duct acoustic effect cannot be considered, directly affecting the accurate determination and low reliability of experimental parametric analysis research.

[0034] Based on the above problems, this embodiment provides an experimental device for parametric research on noise reduction of a ring compressor with a wavy leading edge vane cascade, including a motor, and further including a rotating turbulence generation component 1, a ring compressor vane cascade experimental component 2, and an acoustic mode measurement component 3, all of which are in a rotary body shape; the motor is fixed inside the ring compressor vane cascade experimental component 2 and the acoustic mode measurement component 3, and the motor shaft is fixedly connected to the rotating turbulence generation component 1 to drive the rotating turbulence generation component 1 to rotate; one end of the rotating turbulence generation component 1 is connected to a blowing wind tunnel, and the other end is coaxially docked with the air inlet of the ring compressor vane cascade experimental component 2; the air outlet of the ring compressor vane cascade experimental component 2 is fixedly connected to the air inlet of the acoustic mode measurement component 3 in a coaxial manner;

[0035] The ring compressor vane cascade experimental component 2 includes a vane cascade experimental hub 4, a vane cascade experimental casing 5, a vane cascade experimental vane cascade 6, and a vane cascade cover plate 7; a plurality of blade mounting grooves are radially formed on the side walls of the vane cascade experimental hub 4 and the vane cascade experimental casing 5, and both ends of the experimental vane cascade 6 are respectively embedded in the blade mounting grooves. The vane cascade cover plate 7 is installed in the blade mounting grooves on the vane cascade experimental casing to fix the experimental vane cascade 6 to ensure stable installation and airtightness;

[0036] The acoustic mode measurement component 3 includes an acoustic wave stabilizer 8, an acoustic mode measurement casing 9, and an acoustic mode measurement hub 10, all of which are in a hollow rotary body shape. The acoustic mode measurement hub 10 is located inside the acoustic wave stabilizer 8 and the acoustic mode measurement casing 9 and is coaxially fixedly connected to the vane cascade experimental hub 4. Both ends of the acoustic wave stabilizer 8 are coaxially fixedly connected to the vane cascade experimental casing 5 and the acoustic mode measurement casing 9 respectively. A plurality of microphones are radially installed on the side wall of the acoustic mode measurement hub 10.

[0037] Refer to Figure 7 and Figure 8 ; The experimental vane cascade 6 includes a reference blade and a bionic blade, both of which are in a two-section type and are connected into one body through a set wedge block and wedge groove. The bionic blade includes a bionic blade leading edge 13 and a bionic blade trailing edge 14. One side of the bionic blade leading edge 13 is wavy, and the other side is provided with a wedge-shaped convex block for positioning and fixing with the bionic blade trailing edge 14. The bionic blade leading edge is made by 3D printing. One side of the bionic blade trailing edge 14 is provided with a wedge groove, which is cooperatively connected with the wedge-shaped convex block on the bionic blade leading edge 13. The bionic blade trailing edge 14 is provided with mounting holes along the length direction of the wedge groove for fixedly connecting the connected experimental vane cascade 6 with the vane cascade cover plate 7.

[0038] Refer to Figure 1 and Figure 4, the rotating turbulent flow generating component 1 is generally in the shape of a rotating body, with a central through hole opened along the axis in the middle for connecting the rotating turbulent flow generating component 1 to the motor rotating shaft. The upstream end of the air flow in the turbulent flow generating section 1 is docked with the blowing wind tunnel, and a sound-absorbing lining can be installed between the turbulent flow generating section 1 and the blowing wind tunnel to reduce the influence of the noise generated by the blowing wind tunnel on the measurement results. A plurality of mounting holes are radially opened on the side wall of the rotating turbulent flow generating component 1 for mounting the flow-around round rods 11. On the one hand, the Karman vortex streets of various frequencies are generated by using cylinders of different diameters, and on the other hand, the oncoming turbulent flows of different intensities can be generated, so as to more realistically simulate the rotating / stator interference process of the fan / compressor.

[0039] Refer to Figure 2 ; The annular compressor cascade experimental component 2 includes a cascade experimental hub 4, a cascade experimental casing 5, experimental cascades 6 and cascade covers 7; the cascade experimental hub 4 and the cascade experimental casing 5 are rotating body parts, and a plurality of blade mounting grooves are circumferentially and coaxially opened on the outer wall. The two ends of the experimental cascade 6 are respectively embedded in the blade mounting grooves to connect the cascade experimental hub 4 and the cascade experimental casing. The cascade cover 7 is installed in the blade mounting groove on the cascade experimental casing 5 to fix the experimental cascade 6 and ensure stable blade installation and airtightness of the air flow.

[0040] For facilitating the adjustment and replacement of the number of blades during the experiment, the blade mounting grooves include square mounting grooves and strip mounting grooves. One blade can be installed in the strip groove, and multiple blades can be installed in the square groove. The strip mounting grooves and the strip mounting grooves are arranged at intervals. On the one hand, it can ensure the convenience of replacing the number of blades in the experiment, and on the other hand, it also ensures the strength of the hub and the casing. In order to ensure stable blade installation and airtightness of the air flow, when installing the experimental cascade 6 on the cascade experimental hub 4, filling blocks are installed in the mounting grooves of the cascade experimental section hub 4.

[0041] Refer to Figure 5 ; One end of the cascade cover 7 is a square block, and the other end is a strip block. The side wall of the strip block is curved and matches the side wall of the blade.

[0042] Refer to Figure 3 ; The acoustic mode measurement component 3 includes a sound wave stabilizer 8, an acoustic mode measurement casing 9 and an acoustic mode measurement hub 10, all of which are in the shape of a rotating body with an internal cavity to ensure the stable propagation and measurement of sound waves. The axial length of the sound wave stabilizer 8 is determined by the experimental environment, and the wall surface needs to be smooth. One end of the sound wave stabilizer 8 is coaxially connected to the end face of the cascade experimental casing 5 by bolts, and the other end is coaxially fixedly connected to the acoustic mode measurement casing 9; the acoustic mode measurement hub 10 is located in the cavities of the sound wave stabilizer 8 and the acoustic mode measurement casing 9. One end of the acoustic mode measurement hub 10 is coaxially fixedly connected to the cascade experimental section hub 4. In order to ensure uniform exhaust, the other end of the acoustic mode measurement hub 10 extends out of the cavity of the acoustic mode measurement casing 9, and the other end of the acoustic mode measurement hub 10 is hemispherical.

[0043] On the side wall of the acoustic mode measurement casing 9, a plurality of threaded holes are radially opened for installing microphone probes, and the number of the threaded holes is determined by the acoustic wave frequency, the pipeline geometry and the air flow parameters.

[0044] In order to improve the accuracy of the acoustic test, the acoustic mode measurement assembly 3 can be placed in an anechoic chamber to reduce the background noise of the experimental environment; if there is no anechoic chamber, an acoustic lining can be installed at the outlet of the acoustic mode measurement assembly to reduce the influence of external acoustic waves on the measurement.

[0045] The present invention can also be used for the acoustic lining design experiment. The specific operation is to replace the acoustic wave stabilizer 8 with the designed acoustic lining, and the microphone installed on the casing 9 of the acoustic mode measurement section can be used to parametrically measure the noise reduction effect of various acoustic linings on the wavy leading edge cascade.

[0046] Combined with the actual wind tunnel size of the laboratory, taking the hub radius of the annular cascade pipeline as 130 mm, the casing radius as 190 mm, and the designed air flow velocity as 30 m / s as an example, the determination process of the blade parameters and the number of microphones is as follows:

[0047] 1. Blade parameters

[0048] (1) Determine the blade chord length through the aspect ratio

[0049] In the US HTFC program, the aspect ratio of the benchmark rotor: 1.32; the aspect ratio of the Rotor67 rotor: 1.56. When the wide chord design (small aspect ratio design) is adopted, the aspect ratio is about 1.3. Considering the structural strength and aerodynamic characteristics, the chord length of the annular cascade is set to 50 mm, and the aspect ratio is: 1.2, which is similar to the aspect ratio of the stator blades in the TAAL laboratory of the School of Power and Energy, Northwestern Polytechnical University.

[0050] (2) Determine the number of blades through the compressor solidity

[0051] The general value range of the compressor solidity is between 1.0 and 2.5. When the number of blades is selected as 27, the solidity at the mean diameter is basically the same as that of the stator blades in the TAAL laboratory of the School of Power and Energy, Northwestern Polytechnical University, which is 1.34, and the load coefficient is about 0.8. When the number of blades is selected as 24, the solidity at the mean diameter is 1.194, and the load coefficient is about 0.88.

[0052] For the convenience of experimental processing and the subsequent numerical simulation work, the blade chord length determined in this embodiment is 50 mm, and the number of blades is 24.

[0053] 2. Determination of the number of microphones

[0054] According to the theory of acoustic mode propagation in an annular duct, the highest cut-off mode orders in different directions within the frequency range of interest can be calculated: the maximum circumferential cut-off mode order M and the maximum radial cut-off mode order N. Then, according to the Nyquist sampling theorem, at least 2M + 1 tangential microphone arrays need to be arranged at tangential positions, and at least 2N + 1 spanwise microphone arrays need to be arranged at spanwise positions. At the same time, in order to decompose the incident mode wave and the reflected mode wave, at least two rows of microphone arrays need to be arranged in the axial position.

[0055] According to the dimensions of the above-mentioned annular cascade duct and the flow velocity of the incoming air, the hub radius of the annular cascade duct is 130 mm, the casing radius is 190 mm, and the designed flow velocity of the incoming air is 30 m / s. The maximum cut-off mode orders within the frequency range of 0 - 10,000 Hz can be determined. As Figure 9 shown, within the frequency range of 200 - 5,420 Hz for the annular cascade, the maximum circumferential cut-off mode number is 16, and the maximum radial cut-off mode number is 1. Therefore, a 4×32 microphone array is used for mode decomposition.

[0056] Referring to Figure 10 ; taking the radius of the circular rod around which the flow passes as 1.5 mm, the number as 16, the rotational speed as 2,400 rpm, and the incoming flow velocities as 25 m / s, 50 m / s, and 75 m / s as examples, the noise of the annular cascade is evaluated. The evaluation mainly includes the noise evaluation of the reference configuration and the bionic configuration. The sound power evaluation results of the outlet duct are as Figure 10 shown. For the reference blade and the bionic blade, the sound power level increases with the increase of the incoming flow velocity. Under the same incoming flow velocity, the application of the bionic blade can effectively reduce the noise level in the frequency range of 2,000 Hz - 6,000 Hz. The experimental device of the present invention can accurately evaluate the noise reduction effect of bionic blades of various specifications, improving the applicable range of acoustic experiments on bionic blades.

[0057] Although the embodiments of the present invention have been shown and described above, it can be understood that the above embodiments are exemplary and should not be construed as limiting the present invention. Those of ordinary skill in the art can make changes, modifications, substitutions, and variations to the above embodiments within the scope of the present invention without departing from the principles and purposes of the present invention.

Claims

1. An experimental device for parametric research on noise reduction of a ring compressor with a wavy leading edge blade cascade, comprising a motor, characterized in that, It also includes a rotating turbulent flow generating component (1), an annular compressor cascade experiment component (2), and an acoustic mode measurement component (3), all of which are in the shape of a rotating body; the motor is fixed inside the annular compressor cascade experiment component (2) and the acoustic mode measurement component (3), the motor shaft is fixedly connected to the rotating turbulent flow generating component (1) to drive the rotating turbulent flow generating component (1) to rotate; one end of the rotating turbulent flow generating component (1) is connected to the blowing wind tunnel, and the other end is coaxially butted with the air inlet of the annular compressor cascade experiment component (2); the air outlet of the annular compressor cascade experiment component (2) is fixedly connected to the air inlet of the acoustic mode measurement component (3) coaxially; The annular compressor cascade experiment component (2) includes a cascade experiment hub (4), a cascade experiment casing (5), an experimental cascade (6), and a cascade cover plate (7); a plurality of blade mounting grooves are radially formed on the side walls of the cascade experiment hub (4) and the cascade experiment casing (5), both ends of the experimental cascade (6) are respectively embedded in the blade mounting grooves, and the cascade cover plate (7) is installed in the blade mounting grooves on the cascade experiment casing to fix the experimental cascade (6) to ensure stable installation and airtightness; The acoustic mode measurement component (3) includes an acoustic wave stabilizer (8), an acoustic mode measurement casing (9), and an acoustic mode measurement hub (10), all of which are in the shape of a hollow rotating body. The acoustic mode measurement hub (10) is located inside the acoustic wave stabilizer (8) and the acoustic mode measurement casing (9) and is fixedly connected to the cascade experiment hub (4) coaxially. Both ends of the acoustic wave stabilizer (8) are fixedly connected to the cascade experiment casing (5) and the acoustic mode measurement casing (9) coaxially. A plurality of microphones are radially installed on the side wall of the acoustic mode measurement casing (9); It also includes a flow-around round bar (11); a plurality of mounting holes with different specifications are radially provided on the side wall of the rotating turbulent flow generating component (1), and the flow-around round bar (11) is installed in the mounting holes. Different specifications of flow-around round bars can generate Karman vortex streets with different frequencies and oncoming turbulent flows with different intensities to truly simulate the rotation / stator interference process of a fan / compressor.

2. The experimental device for parametric research on noise reduction of the annular compressor wavy leading-edge blade cascade according to claim 1, wherein, The experimental cascade (6) includes bionic blades. The bionic blades include a bionic blade leading edge (13) and a bionic blade trailing edge (14). One side of the bionic blade leading edge (13) is wavy, and the other side is provided with a wedge-shaped protrusion. One side of the bionic blade trailing edge (14) is provided with a wedge-shaped groove matching the wedge-shaped protrusion on the bionic blade leading edge; mounting holes are provided on the end face of the bionic blade trailing edge (14) along the length direction of the wedge-shaped groove for fixedly connecting the blade to the cascade cover plate (7) to ensure the airtightness of the blade.

3. The experimental device for parametric research on noise reduction of the annular compressor wavy leading-edge blade cascade according to claim 2, characterized in that, The bionic blade leading edge (13) of the bionic blade is made by 3D printing.

4. An experimental device for parametric study on noise reduction of a ring compressor with a wavy leading edge vane cascade, characterized in that, The blade mounting grooves include a plurality of square grooves and strip grooves. The inner walls of the square grooves and strip grooves match the arc surface of the side wall of the experimental cascade, and the square grooves and strip grooves are arranged at intervals.

5. An experimental device for parametric study of noise reduction of a ring compressor with a wavy leading edge vane cascade, characterized in that, To ensure uniform exhaust, the acoustic mode measurement hub (10) extends out of the cavity of the acoustic mode measurement casing (9), and the extending end is hemispherical.

6. The experimental device for parametric study on noise reduction of annular compressor wavy leading edge vane cascade according to claim 1, characterized in that, It also includes filling blocks, which are installed in the blade mounting grooves on the cascade experiment hub (4) to ensure stable installation of the blades when the cascade experiment hub (4) and the experimental cascade (6) are installed and airtight of the air flow.

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