A disc mechanism for a plane cascade test section for controlling an adjustable inlet angle of attack

Abstract

A planar blade cascade test section disc mechanism including a controllable adjustable inlet angle of attack relates to the field of blade cascade wind tunnel testing in the field of impeller machinery. The present invention solves the problem that existing planar blade cascade test machines can only realize flow field tests under the same angle of attack and cannot simulate blade tests at different angles of attack in real flow fields. The inner shell and outer shell of the present invention are connected by multiple connecting limiters, the positioning block assembly is installed on the air inlet side of the inner shell and the outer shell, one end of the upper baffle assembly is rotatably connected to the positioning block assembly, and the lower baffle assembly is slidably matched with the side of the positioning block assembly and moves up and down; the inner disc and the outer disc are rotatably installed on the inner shell and the outer shell respectively, the scale is engraved on the outside of the inner shell, the angle of attack adjustment drive is installed on the outside of the inner disc, and the angle of attack adjustment drive drives the inner disc and the outer disc to rotate simultaneously, realizing the change of the angle of attack of the blade to be tested. The present invention is used for blade cascade wind tunnel testing.

Description

Technical Field

[0001] The invention relates to a disc mechanism, in particular to a disc mechanism comprising a plane cascade test section for controlling an adjustable inlet angle of attack, and belongs to the field of experimental research on aerodynamic performance of impeller machinery. Background Art

[0002] Aircraft need to operate for long periods of time at high altitudes, which requires the engine to be able to operate stably at high altitudes and have low fuel consumption. However, due to the thin air at high altitudes, the compressor inlet pressure and density are significantly reduced. At the same time, the turbofan engine of a high-altitude cruise aircraft is smaller in size, so the compressor inlet Reynolds number is significantly reduced, which leads to a decrease in compressor efficiency and a smaller stable operating range. Studying the performance degradation of the axial flow compressor, a core component of aircraft under high altitude conditions, and the influence of low Reynolds numbers on compressor performance, as well as quantifying the impact of non-design operating conditions at high altitude and low Reynolds numbers on the compressor blade boundary layer, can provide theoretical guidance for correcting the compressor blade loss model under low Reynolds number conditions and the numerical model for predicting the high-altitude low Reynolds number effect of the compressor.

[0003] At low Reynolds numbers, the flow within the blade slots is often laminar or a laminar-turbulent mixed flow state, which can easily cause flow separation on the blade suction surface. In severe cases, this can cause flow blockage, affecting the matching between the compressor and turbine blade rows, resulting in reduced efficiency and performance of engine components, which in turn causes reduced engine thrust, increased fuel consumption, and poor operating stability and reliability, significantly impacting the completion of flight missions. Blade profile research is fundamental and critical to aircraft engine development. To improve overall engine performance, blade profile optimization and improvement of components such as fans, compressors, and turbines is a long-term, iterative process. Plane cascade tests are relatively routine and are conducted more frequently.

[0004] With the continuous deepening of research on the loss characteristics of two-dimensional blade profiles, when testing cascades, blade holes are usually opened on the upper and lower mounting plates, and multiple cascades are installed in the blade holes on the upper and lower mounting plates from top to bottom to form a cascade test piece. The cascade test piece is installed on a flat cascade test machine, and airflow is passed through the cascade test piece to test the performance parameters of the cascade, in order to obtain different blade profile parameters under different Reynolds numbers.

[0005] However, the existing plane blade test machine can only realize the flow field test under the same angle of attack, and there is a problem that it cannot simulate the blade test at different angles of attack under the real flow field. Summary of the Invention

[0006] The present invention aims to address the problem that existing plane cascade testers can only test flow fields at the same angle of attack, and are unable to simulate blade tests at different angles of attack under real flow fields. Furthermore, a plane cascade test section disc mechanism is provided, which includes a control section for controlling an adjustable inlet angle of attack.

[0007] The technical solution of the present invention is:

[0008] A disc mechanism for a plane cascade test section with an adjustable inlet angle of attack includes an inner shell, an outer shell, a positioning block assembly, a plurality of connecting limiters, an inner disc, an outer disc, an angle of attack adjustment drive, an upper baffle assembly, and a lower baffle assembly; the inner shell and the outer shell are connected by a plurality of connecting limiters, the positioning block assembly is installed on the air inlet side of the inner shell and the outer shell, one end of the upper baffle assembly is rotatably connected to the positioning block assembly to be clamped on the cascade on the upper part of the cascade to be tested, and the lower baffle assembly is connected to the positioning block assembly. The side of the component slides and moves up and down to support the lower part of the blade to be tested; the inner disk and the outer disk are rotatably installed on the inner shell and the outer shell respectively, and rectangular holes are respectively opened on the inner disk and the outer disk, wherein the blade to be tested is installed in the rectangular hole, and the scale is engraved on the outside of the inner shell 1 to measure the rotation angle of the inner disk and the outer disk. The angle of attack adjustment drive is installed on the outside of the inner disk, and the angle of attack adjustment drive drives the inner disk and the outer disk to rotate simultaneously to realize the change of the angle of attack of the blade to be tested.

[0009] Furthermore, the positioning block assembly includes an upper positioning block and a lower positioning block, which are fixedly mounted on the air inlet side of the inner shell and the outer shell, and are arranged in parallel.

[0010] Preferably, the end of the lower positioning block is provided with a 45° bevel.

[0011] Furthermore, the connection limiter includes a distance sleeve and a bolt. The bolt passes through the outer shell and is inserted into the distance sleeve between the inner shell and the outer shell, extends out of the inner shell, and is then installed on the inner shell through a nut.

[0012] Furthermore, the attack angle adjustment drive component includes a worm wheel, a worm, a handle, a steering assembly, and a worm mounting seat. The worm wheel is fixedly mounted on the circumferential wall of the outer side of the inner disk, the worm mounting seat is mounted on the inner shell, the worm is rotatably mounted on the worm mounting seat, the steering assembly is mounted on one end of the worm, the handle is connected to the steering assembly, and the handle drives the worm to rotate after being turned through the steering assembly, and the worm is engaged with the worm wheel.

[0013] Furthermore, the upper baffle assembly includes an upper retractable wall plate, a rotating connection, an upper lifting connection and an upper nut screw pair. One end of the upper retractable wall plate is rotatably mounted on the upper positioning block through the rotating connection, the upper nut screw pair is mounted on the inner shell, and the screw end of the upper nut screw pair is connected to the other end of the upper retractable wall plate through the upper lifting connection.

[0014] Furthermore, the lower baffle assembly includes a lower retractable wall panel, two lifting supports, a lower lifting connection and a lower nut screw pair. The curved portion of the lower retractable wall panel is fitted with the end of the lower positioning block and installed on the inner shell, and the lower end of the horizontal portion of the lower retractable wall panel is connected to the lower nut screw pair installed on the inner shell through the lower lifting connection. The two lifting supports are respectively installed on the curved portion and the lower end of the horizontal portion of the lower retractable wall panel.

[0015] Preferably, the aperture of the channel formed between the upper contraction wall plate and the lower contraction wall plate gradually contracts from the air inlet side.

[0016] Furthermore, the lifting support member includes a bracket, a slide rail and a slider. The slide rail is obliquely installed on the inner shell, and the slider is slidably installed on the slide rail. One end of the bracket is connected to the slider, and the other end of the bracket is connected to the lower retractable wall panel.

[0017] Furthermore, it also includes a four-degree-of-freedom displacement mechanism, which is installed on the outer side of the outer shell.

[0018] Compared with the prior art, the present invention has the following effects:

[0019] 1. The present invention installs a cascade test piece on the rectangular holes of the inner and outer discs and secures them to the inner and outer discs with the action of multiple bolts. When installing the cascade test piece, the upper nut-screw pair first drives the upper retractable wall plate to lift through the upper lifting connector. After the cascade test piece is fixed, the end of the upper retractable wall plate is placed on the topmost cascade. The lower retractable wall plate, under the action of the lower nut-screw pair, is pushed upward along the inclined surface of the lower positioning block to drag the lower end of the cascade test piece. When the angle of attack needs to be adjusted for cascade testing, the handle is turned. After the steering assembly turns, the worm is driven to rotate, which in turn drives the worm gear to rotate, and the worm gear drives the inner and outer discs to rotate simultaneously. Since the cascade test piece is installed on the inner and outer discs, the angle of attack of the cascade test piece can be changed by rotating the worm gear while the direction of the inlet airflow remains unchanged, thereby enabling cascade wind tunnel testing of cascades with various angles of attack.

[0020] 2. The upper and lower retractable panels of the present invention are capable of rotation and movement, making them suitable for wind tunnel testing of various cascade blade types. Furthermore, wind tunnel testing of turbine and compressor cascades of varying designs requires only replacing the test blades themselves, while other components remain installed and usable, minimizing testing costs.

[0021] 3. The present invention adopts manual control of the worm gear to achieve effective and high-precision adjustment of the test blade angle, avoiding the failure and adverse problems caused by the use of an electronic control structure in a high temperature environment.

[0022] 4. The test section disc structure of the present invention can change the rotation angle of the adjustable blade cascade. During the blade cascade test, the blade attack angle value of the test blade cascade can be monitored and adjusted, thereby optimizing the adjustable rotation angle blade cascade test process. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 It is an axonometric drawing of the present invention.

[0024] Figure 2 yes Figure 1 Schematic diagram of the structure after removing the four-degree-of-freedom displacement mechanism 23.

[0025] Figure 3 yes Figure 2 Exploded diagram.

[0026] Figure 4 yes Figure 1 Bottom view of .

[0027] Figure 5 It is a structural diagram of the air flow channel.

[0028] Among them, 1. inner shell, 2. outer shell, 3. inner disc, 4. outer disc, 5. rectangular hole, 6. upper positioning block, 7. lower positioning block, 8. distance sleeve, 9. bolt, 10. worm gear, 11. worm, 12. handle, 13. steering assembly, 14. worm mounting seat, 15. upper retractable wall plate, 16. rotating connector, 17. upper lifting connector, 18. upper nut screw pair, 19. lower retractable wall plate, 20. lifting support, 21. lower lifting connector, 22. lower nut screw pair, 23. four-degree-of-freedom displacement mechanism, 20-1. bracket, 20-2. slide rail, 20-3. slider. DETAILED DESCRIPTION

[0029] Specific implementation method 1: Combination Figures 1 to 5Explain this embodiment, this embodiment includes an inner shell 1, an outer shell 2, a positioning block assembly, multiple connection limiters, an inner disc 3, an outer disc 4, an attack angle adjustment drive member, an upper baffle assembly and a lower baffle assembly; the inner shell 1 and the outer shell 2 are connected by multiple connection limiters, the positioning block assembly is installed on the air inlet side of the inner shell 1 and the outer shell 2, one end of the upper baffle assembly is rotatably connected to the positioning block assembly to be clamped on the blade of the upper part of the blade to be tested, and the lower baffle assembly is slidably matched with the side of the positioning block assembly The inner disc 3 and the outer disc 4 are rotatably mounted on the inner shell 1 and the outer shell 2, respectively, and rectangular holes 5 are respectively opened on the inner disc 3 and the outer disc 4, wherein the cascade test piece is mounted in the rectangular hole 5, and scales are engraved on the outer side of the inner shell 1 to measure the rotation angles of the inner disc 3 and the outer disc 4. The angle of attack adjustment drive is mounted on the outer side of the inner disc 3, and the angle of attack adjustment drive drives the inner disc 3 and the outer disc 4 to rotate simultaneously, thereby realizing the change of the angle of attack of the cascade test piece.

[0030] In this embodiment, the rectangular holes 5 formed on the inner and outer disks 3 and 4 are of different sizes, forming stepped rectangular holes. Multiple threaded holes are also formed around the inner and outer disks 3 and 4. Since the distance between the inner and outer disks 3 and 4 is relatively limited in actual use, there are two ways to install the cascade test piece: one is to form the cascade test piece as a single unit and fit it into the stepped rectangular hole; the other is to first attach an upper mounting plate to the inner disk 3 using multiple bolts, then attach multiple cascades to the upper mounting plate, and finally attach the lower mounting plate to the multiple cascades while simultaneously attaching it to the outer disk 4. The entire installation process takes into account that different cascade test pieces are suitable for different installation methods, making testing more flexible.

[0031] In actual use, the inner disc 3 and the outer disc 4 are positioned and connected by multiple latches, ensuring the reliability of the connection between the inner disc 3 and the outer disc 4 and the consistency of the angle during rotation. In addition, the latches between the inner disc 3 and the outer disc 4 are easy and quick to install.

[0032] Specific implementation method 2: Combination Figure 3 and Figure 5 This embodiment describes a positioning block assembly comprising an upper positioning block 6 and a lower positioning block 7. The upper positioning block 6 and the lower positioning block 7 are fixedly mounted on the air inlet side of the inner housing 1 and the outer housing 2, and are arranged parallel to each other. Other components and connections are the same as those in the first embodiment.

[0033] The upper and lower positioning blocks 6 and 7 of this embodiment connect the inner and outer shells 1 and 2, and also serve as air inlets, providing the largest opening in the air intake passage. During installation, bolts connect the upper and lower positioning blocks 6 and 7, as well as the inner and outer shells 1 and 2. The lower positioning block 7 also secures the lower retractable panel, preventing it from shifting during movement.

[0034] Specific implementation method three: Combination Figure 3 and Figure 5 To describe this embodiment, the end of the lower positioning block 7 of this embodiment is provided with a 45° bevel.

[0035] This arrangement ensures that the lower shrinkage wall panel moves along its oblique edge during movement, with smooth transition and high movement precision of the lower shrinkage wall panel. Other components and connection relationships are the same as those in the first or second embodiment.

[0036] Specific implementation method four: Combination Figure 3 To illustrate this embodiment, the connection limiter of this embodiment includes a distance sleeve 8 and a bolt 9. The bolt 9 passes through the outer shell 2 and is inserted into the distance sleeve 8 located between the inner shell 1 and the outer shell 2, and extends out of the inner shell 1, and is then installed on the inner shell 1 through a nut.

[0037] With this arrangement, this embodiment does not directly connect the inner shell 1 and the outer shell 2 with bolts. Instead, a distance sleeve 8 is mounted on the bolts, which not only achieves positioning but also serves as a connection. The other components and connection relationships are the same as any of the specific embodiments 1 to 3.

[0038] This embodiment is also convenient for assembly and disassembly, which is mainly reflected in that when testing different blade cascade test pieces, different lengths of distance sleeves 8 can be selected, which has a wide range of applications and is more flexible. One testing machine can be used to test blade cascades of various models.

[0039] Specific implementation method five: Combination Figure 4 To describe this embodiment, the attack angle adjustment drive component of this embodiment includes a worm wheel 10, a worm 11, a handle 12, a steering assembly 13, and a worm mounting seat 14. The worm wheel 10 is fixedly mounted on the circumferential wall of the outer side of the inner disk 3, the worm mounting seat 14 is mounted on the inner shell 1, the worm 11 is rotatably mounted on the worm mounting seat 14, the steering assembly 13 is mounted on one end of the worm 11, the handle 12 is connected to the steering assembly 13, and the handle 12 drives the worm 11 to rotate after being turned by the steering assembly 13, and the worm 11 is engaged with the worm wheel 10.

[0040] With this arrangement, the angle-of-attack adjustment driver primarily drives the rotation of the inner and outer discs 3 and 4. Since the air inlet passage is fixed, when the rotation angles of the inner and outer discs 3 and 4 change, the airflow impacts the cascade blades at different locations, thereby enabling testing at different angles of attack. The remaining structure and components are identical to any of the first to fourth embodiments.

[0041] In this embodiment, the worm gear 10 uses one-third or one-half of the worm gear strips and is mounted on the inner casing 1 near the air inlet side. In other words, the rotation angle of the cascade test piece is preferably 30°-90°, which can meet the requirements of most angle of attack tests.

[0042] The steering assembly 13 of this embodiment preferably adopts the form of a bevel gear set to achieve steering. The structure is simple and the steering is stable, which is more suitable for high temperature environments.

[0043] This embodiment uses a handle as the driving force instead of a motor or other forms. One reason is that the high temperature environment during the test is taken into consideration, and the motor working at high temperature is prone to adverse effects. The other reason is that manual control can adjust the rotation angle at any time.

[0044] Specific implementation method six: combination Figure 3 To illustrate this embodiment, the upper baffle assembly of this embodiment includes an upper retractable wall panel 15, a rotating connection 16, an upper lifting connection 17 and an upper nut screw pair 18. One end of the upper retractable wall panel 15 is rotatably mounted on the upper positioning block 6 through the rotating connection 16, the upper nut screw pair 18 is mounted on the inner shell 1, and the screw end of the upper nut screw pair 18 is connected to the other end of the upper retractable wall panel 15 through the upper lifting connection 17.

[0045] This arrangement primarily serves to raise and lower the upper retractable panel 15. When raised, it prevents interference with the cascade test piece during installation. When lowered, it abuts the upper portion of the cascade test piece after installation, further securing the cascade. Other components and connections are the same as those in any of the first to third embodiments.

[0046] This embodiment uses an upper nut screw pair 18 to connect the end of the upper contraction wall plate 15, so that the blade can maintain its posture state unchanged during the impact of airflow and achieve self-locking.

[0047] Specific implementation method seven: combination Figure 3To illustrate this embodiment, the lower baffle assembly of this embodiment includes a lower shrinkage wall panel 19, two lifting supports 20, a lower lifting connection member 21 and a lower nut screw pair 22. The curved portion of the lower shrinkage wall panel 19 is fitted with the end of the lower positioning block 7 and installed on the inner shell 1, and the lower end of the horizontal portion of the lower shrinkage wall panel 19 is connected to the lower nut screw pair 22 installed on the inner shell 1 through the lower lifting connection member 21. The two lifting supports 20 are respectively installed on the curved portion and the lower end of the horizontal portion of the lower shrinkage wall panel 19.

[0048] This arrangement facilitates the downward movement of the lower retractable wall plate 19 to hold the cascade test piece. Other components and connection relationships are the same as those in any one of the first to sixth specific embodiments.

[0049] Specific implementation method eight: combination Figure 3 and Figure 5 To illustrate this embodiment, the diameter of the channel formed between the upper contraction wall plate 15 and the lower contraction wall plate 19 is gradually reduced from the air inlet side.

[0050] This arrangement ensures and simulates the actual situation of the airflow entering the cascade test piece in accordance with the model by contracting the intake airflow. The other components are the same as any one of the specific embodiments 1 to 7.

[0051] As a preferred embodiment, the air flow channel in this embodiment has a constant diameter near the cascade test piece, that is, the upper contraction wall panel 15 and the lower contraction wall panel 19 are arranged in parallel.

[0052] Specific implementation method nine: Combination Figure 5 To illustrate this embodiment, the lifting support member 20 of this embodiment includes a bracket 20-1, a slide rail 20-2 and a slider 20-3. The slide rail 20-2 is installed obliquely on the inner shell 1, and the slider 20-3 is slidably installed on the slide rail 20-2. One end of the bracket 20-1 is connected to the slider 20-3, and the other end of the bracket 20-1 is connected to the lower retractable wall panel 19.

[0053] This arrangement facilitates the support of the lower shrinkage wall panel 19, and the lower shrinkage wall panel 19 is smooth and does not get stuck during the lifting and lowering process. The other components are the same as any one of the specific embodiments 1 to 8.

[0054] Furthermore, the slide rail 20 - 2 in this embodiment is installed on the inner shell 1 at an angle of 45°, which matches the structural shape of the lower shrinkage wall panel 19 to ensure that no deviation occurs during the lifting and lowering process of the lower shrinkage wall panel 19.

[0055] Specific implementation method ten: Combination Figure 1 To explain this embodiment, this embodiment further includes a four-degree-of-freedom displacement mechanism 23 , which is mounted on the outer surface of the outer shell 2 .

[0056] Such an arrangement facilitates the accurate movement of the disc mechanism of the present invention to the test position for air intake. The other components are the same as any one of the specific embodiments 1 to 9.

[0057] Combine Figures 1 to 5 To illustrate the working principle of the present invention:

[0058] Assembly of the cascade test piece:

[0059] Blade-shaped holes are opened on the upper mounting plate and the lower mounting plate, and a plurality of blade cascades are sequentially mounted in the blade-shaped holes on the upper mounting plate and the lower mounting plate from top to bottom to form a blade cascade to be tested.

[0060] Installation of cascade test piece:

[0061] The cascade test piece is installed in the rectangular holes of the inner and outer disks by bolts.

[0062] Adjustment of the attack angle of the cascade test piece:

[0063] When the angle of attack needs to be adjusted for cascade testing, the handle is turned. After the steering assembly turns, the worm is driven to rotate, the worm drives the worm wheel to rotate, and the worm wheel drives the inner and outer discs to rotate at the same time. Since the cascade test piece is installed on the inner and outer discs, the angle of attack of the cascade test piece can be changed by rotating the worm wheel while keeping the direction of the inlet airflow unchanged.

[0064] The above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit the same. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the various embodiments of the present invention.

Claims

1. A disc mechanism for a plane cascade test section for controlling an adjustable inlet angle of attack, characterized in that: It comprises an inner shell (1), an outer shell (2), a positioning block assembly, a plurality of connection limiters, an inner disc (3), an outer disc (4), an attack angle adjustment drive member, an upper baffle assembly and a lower baffle assembly; The inner shell (1) and the outer shell (2) are connected by a plurality of connection limiters, the positioning block assembly is installed on the air inlet side of the inner shell (1) and the outer shell (2), one end of the upper baffle assembly is rotatably connected to the positioning block assembly, and is used to be clamped on the blade of the upper part of the blade to be tested, and the lower baffle assembly is slidably matched with the side of the positioning block assembly and moves up and down, and is used to support the lower part of the blade to be tested; The inner disc (3) and the outer disc (4) are rotatably mounted on the inner shell (1) and the outer shell (2), respectively, and rectangular holes (5) are respectively opened on the inner disc (3) and the outer disc (4), wherein the blade to be tested is mounted in the rectangular hole (5), and scales are engraved on the outer side of the inner shell (1) to measure the rotation angles of the inner disc (3) and the outer disc (4), and the angle of attack adjustment driving member is mounted on the outer side of the inner disc (3), and the angle of attack adjustment driving member drives the inner disc (3) and the outer disc (4) to rotate simultaneously, thereby realizing the change of the angle of attack of the blade to be tested; The positioning block assembly comprises an upper positioning block (6) and a lower positioning block (7), wherein the upper positioning block (6) and the lower positioning block (7) are fixedly mounted on the air inlet side of the inner shell (1) and the outer shell (2), and the upper positioning block (6) and the lower positioning block (7) are arranged in parallel; The end of the lower positioning block (7) is provided with a 45° bevel; The connection limiter comprises a distance sleeve (8) and a bolt (9), wherein the bolt (9) passes through the outer shell (2) and is inserted into the distance sleeve (8) between the inner shell (1) and the outer shell (2), and extends out of the inner shell (1), and is then mounted on the inner shell (1) via a nut; The upper baffle assembly includes an upper retractable wall plate (15), a rotating connection member (16), an upper lifting connection member (17) and an upper nut screw pair (18), one end of the upper retractable wall plate (15) is rotatably mounted on the upper positioning block (6) via the rotating connection member (16), the upper nut screw pair (18) is mounted on the inner housing (1), and the screw end of the upper nut screw pair (18) is connected to the other end of the upper retractable wall plate (15) via the upper lifting connection member (17); The lower baffle assembly includes a lower shrinkage wall plate (19), two lifting support members (20), a lower lifting connection member (21) and a lower nut screw pair (22), wherein the curved portion of the lower shrinkage wall plate (19) is affixed to the end of the lower positioning block (7) and is mounted on the inner shell (1), and the lower end of the horizontal portion of the lower shrinkage wall plate (19) is connected to the lower nut screw pair (22) mounted on the inner shell (1) through the lower lifting connection member (21), and the two lifting support members (20) are respectively mounted on the curved portion and the lower end of the horizontal portion of the lower shrinkage wall plate (19); The lifting support member (20) comprises a bracket (20-1), a slide rail (20-2) and a slider (20-3), wherein the slide rail (20-2) is obliquely mounted on the inner shell (1), and the slider (20-3) is slidably mounted on the slide rail (20-2), one end of the bracket (20-1) is connected to the slider (20-3), and the other end of the bracket (20-1) is connected to the lower retractable wall plate (19).

2. A planar cascade test section disc mechanism for controlling an adjustable inlet angle of attack according to claim 1, characterized in that: The attack angle adjustment driving member comprises a worm wheel (10), a worm (11), a handle (12), a steering assembly (13), and a worm mounting seat (14). The worm wheel (10) is fixedly mounted on the circumferential wall of the outer side surface of the inner disc (3). The worm mounting seat (14) is mounted on the inner housing (1). The worm (11) is rotatably mounted on the worm mounting seat (14). The steering assembly (13) is mounted on one end of the worm (11). The handle (12) is connected to the steering assembly (13). After the handle (12) is turned through the steering assembly (13), it drives the worm (11) to rotate, and the worm (11) is meshed with the worm wheel (10).

3. A planar cascade test section disc mechanism for controlling an adjustable inlet angle of attack according to claim 2, characterized in that: The channel aperture formed between the upper contraction wall plate (15) and the lower contraction wall plate (19) gradually contracts from the air inlet side.

4. A planar cascade test section disc mechanism for controlling an adjustable inlet angle of attack according to claim 3, characterized in that: It also includes a four-degree-of-freedom displacement mechanism (23), which is mounted on the outer side of the outer shell (2).

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