Plane cascade test section disc mechanism capable of controlling adjustable inlet attack angle

Abstract

The invention discloses a plane cascade test section disc mechanism capable of controlling an adjustable inlet attack angle, and relates to the cascade wind tunnel test field applied to the turbomachinery field. The problem that an existing plane blade grid testing machine can only achieve flow field tests under the same attack angle and cannot simulate different attack angle tests of blades in a real flow field is solved. An inner shell and an outer shell are connected through a plurality of connecting limiting pieces, a positioning block assembly is installed on the air inlet side of the inner shell and the air inlet side of the outer shell, one end of an upper baffle assembly is rotationally connected with the positioning block assembly, and a lower baffle assembly is in sliding fit with the side face of the positioning block assembly and does lifting motion; the inner disc and the outer disc are rotationally installed on the inner shell and the outer shell respectively, the scales are engraved on the outer side of the inner shell, the attack angle adjusting driving piece is installed on the outer side of the inner disc, the attack angle adjusting driving piece drives the inner disc and the outer disc to rotate at the same time, and the attack angle of the cascade piece to be tested is changed. The method is used for the cascade wind tunnel test.

Description

Technical Field

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

[0002] Aircraft need to operate for a long time in high-altitude environment, which requires the engine to be able to operate stably in high-altitude environment and have the working characteristics of low fuel consumption rate. However, due to the thin air in high-altitude environment, the compressor inlet pressure and density are significantly reduced; at the same time, the turbofan engine of the high-altitude cruise aircraft is small in size, so the compressor inlet Reynolds number is significantly reduced, which leads to a decrease in compressor working efficiency and a reduction in the stable operating range. Studying the performance attenuation of the axial flow compressor, the core component of the aircraft under high-altitude conditions, and the influence of low Reynolds number on the compressor performance, quantifying the impact of non-design conditions on the compressor blade boundary layer under high-altitude low Reynolds number, can provide theoretical guidance for modifying 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] Under low Reynolds number conditions, the flow in the blade slot is often in a laminar or laminar-turbulent mixed flow state, which easily causes flow separation on the blade suction surface. In severe cases, it will 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, poor working stability and reliability, and has a huge impact on the completion of flight missions. Blade profile research is a basic and key work in the development of aircraft engines. In order to improve the overall performance of the engine, the optimization and improvement of the blade profiles 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 the research on the loss characteristics of two-dimensional blades, when testing the cascade, blade holes are usually opened on the upper mounting plate and the lower mounting plate, and multiple blades are installed in the blade holes on the upper mounting plate and the lower mounting plate from top to bottom to form a cascade test piece. The cascade test piece is installed on a plane cascade test machine, and the performance parameters of the cascade are tested by passing airflow through the cascade test piece, in order to obtain different blade parameters under different Reynolds number conditions.

[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 purpose of the present invention is to solve the problem that the existing plane blade cascade test machine can only realize the flow field test under the same angle of attack, and cannot simulate the test of blades at different angles of attack under the real flow field. Further, a plane blade cascade test section disc mechanism including a control of an adjustable inlet angle of attack is provided.

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

[0008] A disc mechanism for a plane blade cascade test section including a control unit for adjusting the inlet attack angle comprises an inner shell, an outer shell, a positioning block assembly, a plurality of connection limiters, an inner disc, an outer disc, an attack angle adjustment driving member, an upper baffle assembly and a lower baffle assembly; the inner shell and the outer shell are connected by a plurality of connection 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 blade cascade at the upper part of the blade cascade to be tested, and the lower baffle assembly is connected to the positioning block assembly The side of the part 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 scales are engraved on the outside of the inner shell 1 to measure the rotation angles of the inner disk and the outer disk. The angle of attack adjustment driving member is installed on the outside of the inner disk, and the angle of attack adjustment driving member 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 with each other.

[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 angle of attack 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 meshed 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 via 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 via the upper lifting connection.

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

[0015] Preferably, the channel aperture 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, 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 the blade to be tested on the rectangular holes of the inner disk and the outer disk, and fixes the blade to be tested on the rectangular holes of the inner disk and the outer disk under the action of multiple bolts. When the blade to be tested is installed, the upper nut screw pair first drives the upper contraction wall plate to be lifted through the upper lifting connection piece. After the blade to be tested is fixed, the end of the upper contraction wall plate is placed on the top of the uppermost blade. Under the action of the lower nut screw pair, the lower contraction wall plate is pushed to move upward along the inclined surface of the lower positioning block to drag the lower end of the blade to be tested. When the angle of attack needs to be adjusted for the blade test, the handle is turned, and after the steering assembly is turned, the worm is driven to rotate, the worm drives the worm wheel to rotate, and the worm wheel drives the inner disk and the outer disk to rotate at the same time. Since the blade to be tested is installed on the inner disk and the outer disk, the angle of attack of the blade to be tested is changed by rotating the worm wheel and the worm under the condition that the direction of the inlet airflow remains unchanged, and the blade wind tunnel test of various angles of attack can be realized.

[0020] 2. The upper and lower contraction panels of the present invention can be rotated and moved, and therefore can be applied to wind tunnel tests of blade cascades of different models. At the same time, for wind tunnel tests of turbine and compressor blade cascades of different designs, only the test blades themselves need to be replaced, and other component structures can still be installed and used, thus saving the test cost to the greatest extent.

[0021] 3. The present invention adopts manually controlled worm gear to realize effective and high-precision adjustment of the test blade angle, avoiding the failure and adverse problems caused by the use of electric control structure in 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 monitoring and adjustment functions of the blade angle of attack of the test blade cascade can be realized, thereby optimizing the adjustable rotation angle blade cascade test process. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 It is an axonometric view 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 schematic 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 connecting part, 17. upper lifting connecting part, 18. upper nut screw pair, 19. lower retractable wall plate, 20. lifting support, 21. lower lifting connecting part, 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 5The present embodiment is described, and the present embodiment 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 angle of attack adjustment drive, 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 to be clamped on the upper part of the cascade 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 provided 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, 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 cascade test piece.

[0030] The rectangular holes 5 opened on the inner disk 3 and the outer disk 4 in this embodiment are of different sizes, forming stepped rectangular holes, and multiple threaded holes are opened around the inner disk 3 and the outer disk 4. Since the distance between the inner disk 3 and the outer disk 4 is relatively limited during actual use, there are two ways to install the cascade test piece: one is to make the cascade test piece into a whole and embed it in the stepped rectangular hole, and the other is to first install the upper mounting plate on the inner disk 3 by multiple bolts, then install multiple cascades on the upper mounting plate, and then install the lower mounting plate on the multiple cascades and on the outer disk 4 at the same time. The entire installation process takes into account that different cascade test pieces are suitable for different installation methods, and the test is more flexible.

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

[0032] Specific implementation method 2: Combination Figure 3 and Figure 5 To explain this embodiment, the positioning block assembly of this embodiment includes an upper positioning block 6 and a lower positioning block 7, which are fixedly mounted on the air inlet side of the inner shell 1 and the outer shell 2, and are arranged in parallel with each other. Other components and connection relationships are the same as those of the first embodiment.

[0033] The upper positioning block 6 and the lower positioning block 7 of this embodiment play a role in connecting the inner shell 1 and the outer shell 2, and also play a role in the airflow inlet, providing the largest diameter part in the air inlet channel. During the installation process, the upper positioning block 6 and the lower positioning block 7 as well as the inner shell 1 and the outer shell 2 are connected by bolts. Under the action of the bolts, the lower positioning block 7 also plays a fixing role, preventing the lower shrinkage wall plate from changing its position during the movement process.

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

[0035] Such arrangement ensures that the lower shrinkage wall plate moves along its bevel during movement, with smooth transition and high movement precision of the lower shrinkage wall plate. Other components and connection relationships are the same as those of the first or second specific implementation.

[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 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] In this way, in the connection mode between the inner shell 1 and the outer shell 2, the present embodiment does not directly use bolts for connection, but a distance sleeve 8 is mounted on the bolt, which can not only realize the positioning function, but also play a connecting role. The other components and connection relationships are the same as any one of the specific embodiments 1 to 3.

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

[0039] Specific implementation method five: Combination Figure 4 To illustrate 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 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, and the handle 12 drives the worm 11 to rotate after being turned by the steering assembly 13, and the worm 11 is meshed with the worm wheel 10.

[0040] In this way, the angle of attack adjustment drive is mainly used to realize the rotation drive of the inner disk 3 and the outer disk 4. Since the air intake channel is fixed, when the rotation angle of the inner disk 3 and the outer disk 4 changes, the airflow impacts the position on the blade cascade at different positions, thereby realizing the test of different angles of attack. The other structures and components are the same as any one of the specific embodiments 1 to 4.

[0041] The worm wheel 10 in this embodiment uses one-third or one-half of the worm wheel strip, and the worm wheel 10 is installed on the inner casing 1 close to the air intake side, that is, the rotation angle of the cascade test piece is preferably 30°-90°. This angle can meet most angle of attack tests.

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

[0043] This embodiment uses a handle as the driving force, and does not use a motor or other forms. One reason is that the high temperature environment during the test process is taken into consideration. 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 plate 15, a rotating connection 16, an upper lifting connection 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 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 plate 15 via the upper lifting connection 17.

[0045] Such a configuration mainly serves to lift and lower the upper shrinkage panel 15. When the upper shrinkage panel 15 is lifted, it is suitable for preventing the upper shrinkage panel 15 from interfering when installing the cascade test piece. When the upper shrinkage panel 15 is lowered, it is suitable for abutting the upper part of the cascade test piece after installing the cascade test piece, thereby further fixing the cascade. Other components and connection relationships are the same as any one of the specific embodiments 1 to 3.

[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 plate 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 plate 19 is attached to 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 plate 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 at the curved portion and the lower end of the horizontal portion of the lower shrinkage wall plate 19.

[0048] Such arrangement facilitates the lower retractable wall plate 19 to move up and down and drag the blade cascade test piece. Other components and connection relationships are the same as any one of the specific embodiments 1 to 6.

[0049] Specific implementation method eight: Combination Figure 3 and Figure 5 To explain this embodiment, in this embodiment, the channel aperture formed between the upper shrink wall plate 15 and the lower shrink wall plate 19 gradually decreases from the air intake side.

[0050] In this way, by contracting the intake airflow, it is ensured and simulated that the airflow entering the cascade test piece conforms to the actual situation of the model. The other components are the same as any one of the specific implementation modes 1 to 7.

[0051] As a preferred manner, the air flow channel in this embodiment has a constant diameter near the cascade test piece, that is, the upper contraction wall plate 15 and the lower contraction wall plate 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 obliquely installed 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] Such arrangement facilitates the support of the lower shrinkage wall plate 19, and the lower shrinkage wall plate 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 installed on the outer side of the outer shell 2 .

[0056] Such arrangement facilitates the disk mechanism of the present invention to be accurately moved to the test position for air intake. The other components are the same as any one of the specific implementation modes 1 to 9.

[0057] Combination 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 the cascade test piece:

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

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

[0063] When the angle of attack needs to be adjusted for the cascade test, the handle is turned, and after the steering assembly is turned, 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 and worm when the direction of the inlet airflow remains 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 the technical solutions described in the aforementioned embodiments may still be modified, or some of the technical features may be replaced by equivalents. 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 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 via a plurality of connection stoppers; a positioning block assembly is mounted 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 cascade at the upper part of the cascade to be tested; and the lower baffle assembly is slidably matched with the side surface of the positioning block assembly and moves up and down and is used to resist the lower part of the cascade to be tested; An inner disc (3) and an outer disc (4) are rotatably mounted on an inner shell (1) and an outer shell (2), respectively, and rectangular holes (5) are respectively opened on the inner disc (3) and the outer disc (4), wherein a blade cascade 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 an 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 a change in the angle of attack of the blade cascade to be tested.

2. A planar cascade test section disc mechanism comprising a controllable inlet angle of attack according to claim 1, characterized in that: 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.

3. A planar cascade test section disc mechanism comprising a controllable inlet angle of attack according to claim 2, characterized in that: The end of the lower positioning block (7) is provided with a 45° bevel.

4. A planar cascade test section disc mechanism comprising a controllable inlet angle of attack according to claim 3, characterized in that: The connection limiter comprises 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) 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.

5. A planar cascade test section disc mechanism comprising a controllable inlet angle of attack according to claim 1 or 4, 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), and the handle (12) drives the worm (11) to rotate after being turned by the steering assembly (13), and the worm (11) is meshed with the worm wheel (10).

6. A planar cascade test section disc mechanism comprising a controllable inlet angle of attack according to claim 5, characterized in that: The upper baffle assembly comprises an upper shrinkage 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 a rotating connection piece (16), an upper nut screw pair (18) is mounted on the inner housing (1), and a screw end of the upper nut screw pair (18) is connected to the other end of the upper retractable wall plate (15) via an upper lifting connection piece (17).

7. A planar cascade test section disc mechanism comprising a controllable inlet angle of attack according to claim 1 or 6, characterized in that: The lower baffle assembly comprises a lower shrinkage wall plate (19), two lifting support members (20), a lower lifting connection member (21) and a lower nut screw pair (22). 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 a lower nut screw pair (22) mounted on the inner shell (1) via a lower lifting connection member (21), and 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).

8. A planar cascade test section disc mechanism for controlling an adjustable inlet angle of attack according to claim 7, 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.

9. A planar cascade test section disc mechanism comprising a controllable inlet angle of attack according to claim 8, characterized in that: The lifting support member (20) comprises a bracket (20-1), a slide rail (20-2) and a slider (20-3); the slide rail (20-2) is obliquely mounted on the inner shell (1); 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).

10. A planar cascade test section disc mechanism comprising a controllable inlet angle of attack according to claim 9, characterized in that: It also includes a four-degree-of-freedom displacement mechanism (23), which is installed on the outer side of the outer shell (2).

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