A test device for simulating unsteady coupled flow in turbine cascades

Abstract

The present invention discloses a test device for simulating unsteady coupled flow in a turbine flat blade cascade. The device comprises a support platform; a power mechanism comprising a drive motor; a wake and cylindrical vortex simulation mechanism comprising a simulation frame and a transmission mechanism, the transmission mechanism comprising a driving gear set, a driven gear set, and a transmission chain set, the transmission chain set being provided with a plurality of titanium alloy cylindrical rods, each of which being provided with a vortex generator; a flat blade cascade test section comprising a test section frame and a blade test piece, the test section frame being provided with an air inlet channel, the blade test piece comprising a blade mounting frame and a flat blade cascade test piece, the flat blade cascade test piece being mounted within the blade mounting frame; and an air inlet mechanism mounted on the wake and cylindrical vortex simulation mechanism, the air inlet mechanism corresponding to the air inlet position of the air inlet channel. The present invention is capable of performing refined simulation of unsteady coupled flow in upstream unsteady wakes and complex vortex systems.

Description

Technical Field

[0001] The invention relates to the technical field of aviation engines, and in particular to a turbine plane blade cascade unsteady coupled flow simulation test device. Background Art

[0002] With the full deployment and implementation of the "Two-Engine Special Plan" for ground-based gas turbines and aircraft engines, the development of domestic aircraft engines continues to advance. As research deepens, more and more technical challenges continue to emerge. Blade wakes and secondary flows in the end region significantly impact turbine machinery losses, aerodynamic stability, noise levels, and vibration characteristics. The periodic unsteady wakes and end region columnar vortices introduced by the upstream rotor are the primary sources of unsteady flow in the turbine cascade channel. Their development in the turbine cascade channel can even affect the flow in downstream multi-stage blade rows. To study the impact of upstream aerodynamic conditions on turbine machinery, a planar cascade test bench with unsteady coupled flow simulation capabilities for blade wakes and columnar vortices, capable of simulating the blades' actual operating environment, is required.

[0003] Considering the complex, time-varying, and tightly coupled nature of turbomachinery inlet aerodynamic conditions in real-world operating environments, existing planar cascade test rigs are limited in functionality, capable only of simulating unsteady wakes without accounting for the complex vortex structures generated by the upstream endwall. This results in low reproducibility for complex incoming flow conditions, limiting their guidance for aerospace turbomachinery design. Furthermore, the wake simulation mechanism in existing test rigs is often mounted alongside the test end, causing the transmission and vibration of the wake mechanism to affect the measured test results in the test section. Summary of the Invention

[0004] In view of the above-mentioned deficiencies in the prior art, the technical problem to be solved by the present invention is: how to provide a turbine plane blade unsteady coupled flow simulation test device that can perform fine simulation of upstream unsteady wakes and unsteady coupled flows of complex vortex systems.

[0005] In order to solve the above technical problems, the present invention adopts the following technical solutions:

[0006] A turbine plane blade cascade unsteady coupled flow simulation test device, comprising:

[0007] Support table;

[0008] A power mechanism, the power mechanism comprising a drive motor;

[0009] A wake and cylindrical vortex simulation mechanism, wherein the wake and cylindrical vortex simulation mechanism is installed on the support platform, and the wake and cylindrical vortex simulation mechanism includes a simulation frame and a transmission mechanism, wherein the transmission mechanism includes a driving gear set, a driven gear set and a transmission chain set, the driving gear set is connected to the driving motor so that the driving motor can drive the driving gear set to rotate, the driving gear set and the driven gear set are connected through the transmission chain set so that the driving gear set, the driven gear set and the transmission chain set are synchronously transmitted, and a plurality of titanium alloy cylindrical rods are further provided on the transmission chain set along the transmission direction of the transmission chain set, and a vortex generator is further provided on each of the titanium alloy cylindrical rods, and the vortex generator and the titanium alloy cylindrical rod are synchronously transmitted following the transmission chain;

[0010] A plane cascade test section, the plane cascade test section being mounted on the support platform, the plane cascade test section comprising a test section frame and a blade test piece, the test section frame being provided with an air inlet channel, the blade test piece comprising a blade mounting frame and a plane cascade test piece, the blade mounting frame being provided at the air outlet position of the air inlet channel, and the plane cascade test piece being mounted within the blade mounting frame;

[0011] An air inlet mechanism is installed on the wake and cylindrical vortex simulation mechanism, and the air inlet mechanism corresponds to the air inlet position of the air inlet channel.

[0012] The working principle of this scheme is as follows: the plane blade test piece is installed in the blade mounting frame, the air flow enters the air inlet channel from the air inlet mechanism, the drive motor is started, the drive motor rotates and drives the driving gear set to rotate, the rotation of the driving gear set further drives the driven gear set and the transmission chain set to rotate, and while the transmission chain set rotates, the titanium alloy cylindrical rod and the vortex generator follow the rotation. During the entire rotation process, the gas from the air inlet mechanism flows to the plane blade test piece through the air inlet channel, and the transmission chain set drives the titanium alloy cylindrical rod to rotate to generate a wake. At the same time, the incoming gas will generate a series of vortex structures when passing through the rotating vortex generator, thereby realizing the unsteady coupled flow simulation of the upstream wake of the plane blade and the columnar complex vortex system in the blade tip area.

[0013] Preferably, the driving gear group includes a first driving gear and a second driving gear that are arranged vertically and rotate synchronously, the driven gear group includes a first driven gear and a second driven gear that are arranged vertically and rotate synchronously, the transmission chain group includes a first transmission chain and a second transmission chain that are arranged vertically and rotate synchronously, the first transmission chain is sleeved on the first driving gear and the first driven gear, the second transmission chain is sleeved on the second driving gear and the second driven gear, and the vertical ends of the titanium alloy cylindrical rod are respectively connected to the first transmission chain and the second transmission chain at corresponding positions.

[0014] Preferably, the vortex generator is located at the upper end of the titanium alloy cylindrical rod at the corresponding position, the lower end face of the vortex generator is fixedly connected to the titanium alloy cylindrical rod, the upper end face of the vortex generator is the vortex generating surface, and the two sides of the vortex generator along the movement direction of the vortex generator are the leading edge of the vortex generator and the trailing edge of the vortex generator respectively.

[0015] Preferably, the arc length of the lower end surface of the vortex generator is C2, the leading edge intersection point formed by the leading edge of the vortex generator and the vortex generating surface is J, the trailing edge intersection point formed by the trailing edge of the vortex generator and the vortex generating surface is K, and the two side surfaces of the vortex generator are vertical planes parallel to each other, and the height of the side surface on the leading edge side of the vortex generator is A1, and the height of the side surface on the trailing edge side of the vortex generator is A2.

[0016] Preferably, the width of the vortex generating surface is B1, the length of the vortex generating surface is C1, the vortex generating surface is an inclined surface, and the angle between the inclined surface and the horizontal plane is α.

[0017] Preferably, the leading edge of the vortex generator is located on the front side of the movement direction of the titanium alloy cylindrical rod, and the trailing edge of the vortex generator is located on the trailing side of the movement direction of the titanium alloy cylindrical rod, and the distance between the leading edge intersection J and the upper end face of the titanium alloy cylindrical rod is H1, the distance between the leading edge intersection J and the front side edge of the movement direction of the titanium alloy cylindrical rod is D1, and the distance between the trailing edge intersection K and the upper end face of the titanium alloy cylindrical rod is H2.

[0018] Preferably, a shock-absorbing mechanism is provided on both sides of the air inlet channel along the air flow direction, and the shock-absorbing mechanism includes a shock-absorbing block, and a shock-absorbing groove is provided on the shock-absorbing block. The transmission chain group passes through the shock-absorbing groove on the shock-absorbing block at the corresponding position, and the size of the shock-absorbing groove is adapted to the size of the corresponding position of the transmission chain group.

[0019] Preferably, the turbine plane blade unsteady coupled flow simulation test device also includes a transmission support mechanism, and the transmission support mechanism includes a first transmission support assembly and a second transmission support assembly fixed on the support platform, the first transmission support assembly is connected to the driving gear set through a driving shaft, and the second transmission support assembly is connected to the driven gear set through a driven shaft.

[0020] Preferably, a plurality of the titanium alloy cylindrical rods are installed on the transmission chain assembly at equal intervals.

[0021] Preferably, a mounting hole is provided on the simulation frame at a position corresponding to the driven wheel set, and a photoelectric rotation speed measuring instrument is installed at the mounting hole.

[0022] Compared with the prior art, the present invention has the following advantages:

[0023] 1. The present invention installs several titanium alloy cylindrical rods with vortex generators between two transmission chains. The drive motor drives the transmission chain group to rotate, and then the transmission chain group drives the titanium alloy cylindrical rods to move and generate wakes. At the same time, the present invention innovatively applies vortex generators to the wake and cylindrical vortex simulation mechanism. When the airflow passes through different vortex generators, a series of vortex structures will be generated, thereby realizing the unsteady coupled flow simulation of the upstream wake of the plane blade cascade and the columnar complex vortex system in the blade tip area.

[0024] 2. The present invention generates less excitation in the transmission chain under high-speed operation, and the titanium alloy cylindrical rod will not be blown off, thereby realizing wake simulation under high Mach numbers. The Mach number in the experiment can reach the data under real working conditions.

[0025] 3. The present invention separates the plane blade test section and the wake and cylindrical vortex simulation mechanism during assembly, and installs shock-absorbing devices on both the front and rear sides of the air inlet channel in the direction of airflow. The shock-absorbing devices are used to cover the surface of the transmission chain group at the interface between the wake and cylindrical vortex simulation mechanism and the plane blade test section. On the one hand, this ensures the smooth operation of the transmission chain group, and on the other hand, it eliminates the influence of the test bench vibration and mechanism transmission on the test results of the plane blade test piece, making the test results closer to the actual operation results.

[0026] 4. In the present invention, the blade mounting frame is provided with several rows of mounting holes corresponding to the plane cascade test piece. With the help of external tools, the plane cascade test piece can adjust the geometric parameters of the test section cascade inlet simply, accurately and labor-savingly. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Attachment Figure 1 Schematic diagram of the structure of the unsteady coupled flow simulation test device of the turbine plane blade cascade of the present invention;

[0028] Attachment Figure 2 Schematic diagram of the structure of the unsteady coupled flow simulation test device for the turbine plane blade cascade of the present invention (after removing the upper part of the simulation frame);

[0029] Attachment Figure 3 This is a front view of the unsteady coupled flow simulation test device for a turbine plane blade cascade according to the present invention (with the upper portion of the simulation frame removed);

[0030] Attachment Figure 4 Schematic diagram of the structure of the wake and cylindrical vortex simulation mechanism in the unsteady coupled flow simulation test device of the turbine plane blade cascade of the present invention (after removing the upper part of the simulation frame);

[0031] Attachment Figure 5 Schematic diagram of the structure of the titanium alloy cylindrical rod in the unsteady coupled flow simulation test device of the turbine plane blade cascade of the present invention;

[0032] Attachment Figure 6 Schematic diagram of the structure and dimensions of the vortex generator in the unsteady coupled flow simulation test device of the turbine plane blade cascade of the present invention;

[0033] Attachment Figure 7 Schematic diagram of the installation position of the vortex generator in the unsteady coupled flow simulation test device of the turbine plane blade cascade of the present invention;

[0034] Attachment Figure 8 This is a schematic structural diagram of a support platform in a test device for simulating unsteady coupled flow of a turbine plane cascade according to the present invention;

[0035] Attachment Figure 9 Schematic diagram of the structure of the transmission support mechanism (with mounting platform) in the unsteady coupled flow simulation test device for the turbine plane blade cascade of the present invention;

[0036] Attachment Figure 10 This is a schematic structural diagram of a plane blade cascade test section in a turbine plane blade cascade unsteady coupled flow simulation test device according to the present invention;

[0037] Attachment Figure 11 The figure is a schematic structural diagram of the power mechanism in the unsteady coupled flow simulation test device of the turbine plane blade grid of the present invention.

[0038] Explanation of the accompanying drawings: bracket 1, base 11, bracket 12, reinforcement block 13, mounting platform 14, wake and cylindrical vortex simulation mechanism 2, driven gear group 21, first driven gear 211, second driven gear 212, driving gear group 22, first driving gear 221, second driving gear 222, transmission chain group 23, first transmission chain 231, second transmission chain 232, titanium alloy cylindrical rod 24, simulation frame 25, vortex generator 26, plane blade test section 3, air inlet channel 31, blade mounting frame 32, test section frame 33, adjustable cover plate 34, plane blade test piece 4, power mechanism 5, motor mounting seat 51, drive motor 52, transmission support mechanism 6, second transmission support assembly 61, first transmission support assembly 62, photoelectric speed measuring instrument 7, shock absorber block 8. DETAILED DESCRIPTION

[0039] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. The components of the embodiments of the present invention generally described and shown in the drawings herein can be arranged and designed in various different configurations. Therefore, the following detailed description of the embodiments of the present invention provided in the drawings is not intended to limit the scope of the invention claimed for protection, but merely represents selected embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present invention.

[0040] It should be noted that similar reference numerals and letters denote similar items in the following figures. Therefore, once an item is defined in one figure, it does not require further definition or explanation in subsequent figures. In the description of the present invention, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the figures, or the orientations or positional relationships in which the inventive product is typically placed when in use. These terms are intended solely to facilitate the description of the present invention and simplify the description. They do not indicate or imply that the devices or components referred to must have a specific orientation, be constructed, or operate in a specific orientation, and are therefore not to be construed as limiting the present invention. Furthermore, the terms "first," "second," and "third," etc., are used solely to distinguish descriptions and are not to be construed as indicating or implying relative importance. Furthermore, terms such as "horizontal" and "vertical" do not imply that a component must be absolutely horizontal or overhanging, but rather may be slightly tilted. For example, "horizontal" simply refers to a direction that is more horizontal than "vertical," and does not imply that the structure must be completely horizontal, but rather may be slightly tilted. In the description of the present invention, it should also be noted that, unless otherwise expressly specified or limited, the terms "disposed," "installed," "connected," and "connected" should be understood in a broad sense. For example, they may refer to fixed connections, detachable connections, or integral connections; they may refer to mechanical connections or electrical connections; they may refer to direct connections or indirect connections through an intermediate medium; and they may refer to internal communication between two components. Those skilled in the art will understand the specific meanings of the above terms in the present invention based on the specific circumstances.

[0041] As attached Figure 1 To the attached Figure 11 As shown, the present invention provides a turbine plane blade unsteady coupled flow simulation test device, including a support platform 1, a power mechanism 5, a wake and cylindrical vortex simulation mechanism 2, a plane blade test section 3, an air inlet mechanism and a transmission support mechanism 6.

[0042] Among them, the support platform 1 includes a support 12 and a base 11. The support 12 includes multiple oblique supports and multiple vertical supports. Each support is fixedly connected to the base 11, and a reinforcement block 13 is provided at the connection between each support to improve the strength of the entire support platform 1. A mounting platform 14 is also fixed at the top of the support platform 1.

[0043] The power mechanism 5 includes a drive motor 52 and a motor mounting base 51. The motor mounting base 51 is fixedly connected to the support platform 1. The drive motor 52 is fixed on the motor mounting base 51. The drive motor 52 adopts a variable frequency motor. The drive motor 52 is also connected to the driving gear set 22 in the cylindrical vortex simulation mechanism 2 through a belt and a wake.

[0044] The wake and cylindrical vortex simulation mechanism 2 is installed on the support platform 1. The wake and cylindrical vortex simulation mechanism 2 includes a simulation frame 25 and a transmission mechanism. The transmission mechanism is located in the simulation frame 25. The transmission mechanism includes a driving gear set 22, a driven gear set 21 and a transmission chain set 23. The driving gear set 22 and the driven gear set 21 are respectively located on the left and right sides of the length direction of the simulation frame 25. The driving gear set 22 is connected to the driving motor 52 so that the driving motor 52 can drive the driving gear set 22 to rotate. The driving gear set The driving gear set 22 and the driven gear set 21 are connected in transmission through the transmission chain set 23, so that the driving gear set 22, the driven gear set 21 and the transmission chain set 23 are synchronously transmitted. A plurality of titanium alloy cylindrical rods 24 are also provided on the transmission chain set 23 along the transmission direction of the transmission chain set 23. The plurality of titanium alloy cylindrical rods 24 are installed on the transmission chain set 23 at equal intervals. A vortex generator 26 is also provided on each titanium alloy cylindrical rod 24. The vortex generator 26 and the titanium alloy cylindrical rod 24 are synchronously transmitted following the transmission chain.

[0045] Specifically, the driving gear set 22 includes a first driving gear 221 and a second driving gear 222 that are vertically arranged and rotate synchronously, the driven gear set 21 includes a first driven gear 211 and a second driven gear 212 that are vertically arranged and rotate synchronously, and the transmission chain set 23 includes a first transmission chain 231 and a second transmission chain 232 that are vertically arranged and rotate synchronously. The first transmission chain 231 is sleeved on the first driving gear 221 and the first driven gear 211, and the second transmission chain 232 is sleeved on the second driving gear 222 and the second driven gear 212. The vertical ends of the titanium alloy cylindrical rod 24 are respectively connected to the first transmission chain 231 and the second transmission chain 232 at corresponding positions.

[0046] In this embodiment, the vortex generator 26 is located at the upper end of the titanium alloy cylindrical rod 24 at the corresponding position, the lower end face of the vortex generator 26 is fixedly connected to the titanium alloy cylindrical rod 24, the upper end face of the vortex generator 26 is the vortex generating surface, and the two sides of the vortex generator 26 along the movement direction of the vortex generator 26 are the leading edge of the vortex generator 26 and the trailing edge of the vortex generator 26 respectively.

[0047] Specifically, as attached Figure 6 and attached Figure 7As shown, the arc length of the lower end surface of vortex generator 26 is C2, the intersection point of the leading edge of vortex generator 26 and the leading edge of the vortex generating surface is J, and the intersection point of the trailing edge of vortex generator 26 and the trailing edge of the vortex generating surface is K. The two side surfaces of vortex generator 26 are parallel vertical surfaces, and the height of the side surface on the leading edge side of vortex generator 26 is A1, and the height of the side surface on the trailing edge side of vortex generator 26 is A2. The width of the vortex generating surface is B1, the length of the vortex generating surface is C1, and the vortex generating surface is an inclined surface, with an angle α between the inclined surface and the horizontal plane. The leading edge of the vortex generator 26 is located on the front side of the movement direction of the titanium alloy cylindrical rod 24, and the trailing edge of the vortex generator 26 is located on the trailing side of the movement direction of the titanium alloy cylindrical rod 24. The distance between the leading edge intersection J and the upper end surface of the titanium alloy cylindrical rod 24 is H1, the distance between the leading edge intersection J and the front edge of the movement direction of the titanium alloy cylindrical rod 24 is D1, and the distance between the trailing edge intersection K and the upper end surface of the titanium alloy cylindrical rod 24 is H2.

[0048] Specifically, the plane vane test section 3 is installed on the support platform 1. The plane vane test section 3 includes a test section frame 33 and a blade test piece. The test section frame 33 is provided with an air inlet channel 31 in the middle of the transmission chain group 23. The test section frame 33 is installed with an adjustable cover plate 34 on the rear side of the wake and cylindrical vortex simulation mechanism 2. The blade test piece includes a blade mounting frame 32 and a plane vane test piece 4. The blade mounting frame 32 is installed on the rear side of the adjustable cover plate 34. The blade mounting frame 32 corresponds to the air outlet position of the air inlet channel 31. Several rows of mounting holes corresponding to the plane vane test piece 4 are opened on the blade mounting frame 32. The upper end of the plane vane test piece 4 vertically passes through the mounting hole and is inserted into the blade mounting frame 32, so that the plane vane test piece 4 is installed in the blade mounting frame 32.

[0049] In this embodiment, the air inlet mechanism is installed on the wake and cylindrical vortex simulation mechanism 2 , and the air inlet mechanism corresponds to the air inlet position of the air inlet channel 31 , so that the air flow can enter the air inlet channel 31 from the air inlet mechanism.

[0050] In this embodiment, a shock-absorbing mechanism is provided on both sides of the air inlet channel 31 along the air flow direction. The shock-absorbing mechanism includes a shock-absorbing block 8, which is made of polytetrafluoroethylene shock-absorbing material. A shock-absorbing groove is provided on the shock-absorbing block 8. The transmission chain group 23 passes through the shock-absorbing groove on the shock-absorbing block 8 at the corresponding position, and the size of the shock-absorbing groove is adapted to the size of the corresponding position of the transmission chain group 23. In this way, the transmission chain can pass through the shock-absorbing groove smoothly, and at the same time, the surface of the transmission chain group 23 at the interface between the wake and the cylindrical vortex simulation mechanism 2 and the plane blade test section 3 can be covered. On the one hand, the smooth operation of the transmission chain group 23 can be ensured, and on the other hand, the influence of the test bench vibration and mechanism transmission on the test results of the plane blade test piece 4 is eliminated, so that the test results are closer to the actual operation results.

[0051] In this embodiment, the transmission support mechanism includes a first transmission support assembly 62 and a second transmission support assembly 61 fixed on the support platform 1, the first transmission support assembly 62 is connected to the driving gear set 22 through a driving shaft, the driving shaft is connected to the power mechanism 5 through a belt, and the first driving gear 221 and the second driving gear 222 are both fixedly mounted on the driving shaft, and the driving shaft is connected to the first transmission support assembly 62 through a spherical roller bearing, the second transmission support assembly 61 is connected to the driven gear set 21 through a driven shaft, and the first driven gear 211 and the second driven gear 212 are both fixedly mounted on the slave shaft, and the slave shaft is connected to the second transmission support assembly 61 through a spherical roller bearing.

[0052] In this embodiment, a mounting hole is provided on the simulation frame 25 at a position corresponding to the driven wheel set, and a photoelectric rotation speed measuring instrument 7 is installed at the mounting hole.

[0053] The working principle of this solution is as follows: when conducting a turbine plane blade unsteady coupled flow simulation test, the plane blade test piece 4 is installed in the blade mounting frame 32, the airflow enters the air inlet channel 31 from the air inlet mechanism, the drive motor 52 is started, the drive motor 52 rotates and drives the driving shaft to rotate through the belt, the driving shaft rotates and drives the first driving gear 221 and the second driving gear 222 to rotate, when the first driving gear 221 rotates, it drives the first driven gear 211 to rotate through the first transmission chain 231, and the second driving gear 222 rotates through the second transmission chain 232 Drive the second driven gear 212 to rotate. When the first transmission chain 231 and the second transmission chain 232 rotate, the titanium alloy cylindrical rod 24 and the vortex generator 26 will rotate synchronously. During the entire rotation process, the air inlet mechanism gas flows to the plane blade test section 3 through the air inlet channel 31. When the incoming gas passes through the several titanium alloy cylindrical rods 24 with vortex generators 26 driven by the driving motor 52 in the wake and cylindrical vortex simulation mechanism 2, a wake and cylindrical vortex system coupling flow will be generated, thereby realizing the flow simulation of the upstream wake of the plane blade and the end area cylindrical vortex system.

[0054] The present invention installs several titanium alloy cylindrical rods 24 equipped with vortex generators 26 between two transmission chains. A drive motor 52 drives the transmission chain assembly 23 to rotate, which in turn drives the titanium alloy cylindrical rods 24 to move and generate wakes. The present invention also innovatively incorporates the vortex generators 26 into the wake and cylindrical vortex simulation mechanism 2. When airflow passes through different vortex generators 26, a series of vortex structures are generated, thereby achieving unsteady coupled flow simulation of the upstream wake of a planar cascade and the complex cylindrical vortex system at the blade tip. Furthermore, the present invention can simulate wakes at high Mach numbers, achieving experimental Mach numbers comparable to those found under real operating conditions. The present invention separates the planar cascade test section 3 and the wake and cylindrical vortex simulation mechanism 2 during assembly, and installs shock absorbers on both the front and rear sides of the airflow direction of the inlet channel 31. The shock absorbers cover the surface of the transmission chain assembly 23 at the interface between the wake and cylindrical vortex simulation mechanism 2 and the planar cascade test section 3. This not only ensures the smooth operation of the transmission chain assembly 23, but also eliminates the impact of test bench vibration and mechanism transmission on the test results of the planar cascade test piece 4, making the test results closer to actual operating results. In the present invention, the blade mounting frame 32 is provided with several rows of mounting holes corresponding to the planar cascade test piece 4. With the help of external tools, the planar cascade test piece 4 can adjust the geometric parameters of the test section cascade inlet simply, accurately, and labor-savingly.

[0055] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention rather than to limit the technical solutions. Those skilled in the art should understand that modifications or equivalent replacements of the technical solutions of the present invention that do not depart from the purpose and scope of the technical solutions of the present invention should be included in the scope of the claims of the present invention.

Claims

1. A turbine plane blade cascade unsteady coupled flow simulation test device, characterized in that: include: Support table; A power mechanism, the power mechanism comprising a drive motor; The wake and cylindrical vortex simulation mechanism is installed on the support platform, and the wake and cylindrical vortex simulation mechanism includes a simulation frame and a transmission mechanism. The transmission mechanism includes a driving gear set, a driven gear set and a transmission chain set. The driving gear set is connected to the driving motor so that the driving motor can drive the driving gear set to rotate. The driving gear set and the driven gear set are connected through the transmission chain set so that the driving gear set, the driven gear set and the transmission chain set are synchronously driven. The transmission chain group is further provided with a plurality of titanium alloy cylindrical rods along the transmission direction of the transmission chain group, and a vortex generator is further provided on each of the titanium alloy cylindrical rods, and the vortex generator and the titanium alloy cylindrical rod are synchronously driven following the transmission chain; the vortex generator is located at the upper end of the titanium alloy cylindrical rod at the corresponding position, the lower end surface of the vortex generator is fixedly connected to the titanium alloy cylindrical rod, the upper end surface of the vortex generator is a vortex generating surface, and the two sides of the vortex generator along the movement direction of the vortex generator are respectively the leading edge and the trailing edge of the vortex generator; A plane cascade test section, the plane cascade test section being mounted on the support platform, the plane cascade test section comprising a test section frame and a blade test piece, the test section frame being provided with an air inlet channel, the blade test piece comprising a blade mounting frame and a plane cascade test piece, the blade mounting frame being provided at the air outlet position of the air inlet channel, and the plane cascade test piece being mounted within the blade mounting frame; An air intake mechanism is installed on the wake and cylindrical vortex simulation mechanism, and the air intake mechanism corresponds to the air inlet position of the air inlet channel; a shock absorbing mechanism is provided on both sides of the air inlet channel along the air flow direction, and the shock absorbing mechanism includes a shock absorbing block, and a shock absorbing groove is provided on the shock absorbing block. The transmission chain group passes through the shock absorbing groove on the shock absorbing block at the corresponding position, and the size of the shock absorbing groove is adapted to the size of the corresponding position of the transmission chain group.

2. The unsteady coupled flow simulation test device for turbine plane blade cascade according to claim 1, characterized in that: The driving gear set includes a first driving gear and a second driving gear arranged vertically and rotating synchronously, the driven gear set includes a first driven gear and a second driven gear arranged vertically and rotating synchronously, the transmission chain set includes a first transmission chain and a second transmission chain arranged vertically and rotating synchronously, the first transmission chain is sleeved on the first driving gear and the first driven gear, the second transmission chain is sleeved on the second driving gear and the second driven gear, and the vertical ends of the titanium alloy cylindrical rod are respectively connected to the first transmission chain and the second transmission chain at corresponding positions.

3. The unsteady coupled flow simulation test device for a turbine plane blade cascade according to claim 1, characterized in that: The arc length of the lower end surface of the vortex generator is C2, the leading edge intersection point formed by the leading edge of the vortex generator and the vortex generating surface is J, the trailing edge intersection point formed by the trailing edge of the vortex generator and the vortex generating surface is K, the two side surfaces of the vortex generator are vertical planes parallel to each other, and the height of the side surface on the leading edge side of the vortex generator is A1, and the height of the side surface on the trailing edge side of the vortex generator is A2.

4. The unsteady coupled flow simulation test device for a turbine plane blade cascade according to claim 3, characterized in that: The width of the vortex generating surface is B1, the length of the vortex generating surface is C1, the vortex generating surface is an inclined surface, and the angle between the inclined surface and the horizontal plane is α.

5. The unsteady coupled flow simulation test device for a turbine plane blade cascade according to claim 3, characterized in that: The leading edge of the vortex generator is located on the front side of the movement direction of the titanium alloy cylindrical rod, and the trailing edge of the vortex generator is located on the trailing side of the movement direction of the titanium alloy cylindrical rod. The distance between the leading edge intersection J and the upper end face of the titanium alloy cylindrical rod is H1, the distance between the leading edge intersection J and the front edge of the movement direction of the titanium alloy cylindrical rod is D1, and the distance between the trailing edge intersection K and the upper end face of the titanium alloy cylindrical rod is H2.

6. The unsteady coupled flow simulation test device for a turbine plane blade cascade according to claim 1, characterized in that: The turbine plane blade unsteady coupled flow simulation test device also includes a transmission support mechanism, which includes a first transmission support assembly and a second transmission support assembly fixed to the support platform, the first transmission support assembly is connected to the driving gear set through a driving shaft, and the second transmission support assembly is connected to the driven gear set through a driven shaft.

7. The unsteady coupled flow simulation test device for a turbine plane blade cascade according to claim 1, characterized in that: A plurality of titanium alloy cylindrical rods are installed on the transmission chain assembly at equal intervals.

8. The unsteady coupled flow simulation test device for a turbine plane blade cascade according to claim 2, characterized in that: A mounting hole is provided on the simulation frame at a position corresponding to the driven gear set, and a photoelectric rotation speed measuring instrument is installed at the mounting hole.

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