A multi-row turbine plane cascade test device with wake excitation and a test method

Abstract

The present disclosure relates to the technical field of test design, and discloses a multi-row turbine planar cascade test device with wake excitation and a test method. The test device comprises a first grid plate, a second grid plate, turbine blades, excitation blades, a driving structure, a pressure test assembly and strain gauges. The turbine blades are composed of a boss and a blade body, the boss is detachably connected with the first grid plate, and the second grid plate is spaced apart from the end of the blade body. The excitation blades can reciprocate along a first direction parallel to the surface of the first grid plate and are driven by the driving structure. The reciprocating movement of the excitation blades forms periodic airflow excitation, simulating a real turbine wake flow field. The pressure test assembly in the blade body detects dynamic pressure, and the surface strain gauges collect strain parameters, so that multi-parameter synchronous measurement under fluid-structure coupling effect can be realized. The device can truly reproduce the service working condition of the turbine blade, has high test precision and good working condition restoration degree, and can provide reliable test basis for the design, strength checking and life evaluation of the aero-engine blade.

Description

Technical Field

[0001] This disclosure relates to the field of experimental design technology, and more specifically, to a test apparatus and test method for a multi-row turbine planar blade cascade with wake excitation. Background Technology

[0002] During the actual operation of aero-engine turbomachinery, periodic wake interference occurs between the moving blades and the stationary blades. When the moving blades sweep past the stationary blades, regular wake shedding and airflow disturbances are generated, subjecting the stationary blade surface to alternating aerodynamic loads and inducing blade structural deformation. This, in turn, creates a complex fluid-structure interaction effect with the flow field. This interaction directly affects the structural strength, vibration characteristics, and fatigue life of the turbine blades, making it a key research area for turbine blade aerodynamic design and strength verification.

[0003] In related technologies, experimental studies on turbine blades often employ static loading or a single uniform airflow condition, which makes it difficult to realistically reproduce the periodic wake excitation environment generated by rotating blades inside the engine. Therefore, there is an urgent need for an experimental device that can simulate real wake excitation and accurately reproduce fluid-structure interaction conditions.

[0004] It should be noted that the information disclosed in the background section above is only used to enhance the understanding of the background of this disclosure, and therefore may include information that does not constitute prior art known to those skilled in the art. Summary of the Invention

[0005] This disclosure provides a test apparatus and test method for a multi-row turbine planar blade cascade with wake excitation.

[0006] According to one aspect of this disclosure, a test apparatus for a multi-row turbine planar blade cascade with wake excitation is provided, comprising: First grid plate; The turbine blade includes an integrally formed boss and blade body, wherein the boss is detachably connected to the first grid plate; The second grid plate is disposed on the side of the blade away from the first grid plate and is connected to the first grid plate. The second grid plate has a gap with the end of the blade away from the boss. The excitation blade is located between the first grid plate and the second grid plate, and can reciprocate along a first direction, which is parallel to the length direction of the first grid plate. A driving structure is provided for driving the excitation blade to reciprocate along the first direction. A pressure testing component is disposed inside the blade body. When the excitation blade reciprocates relative to the turbine blade along the first direction, the pressure testing component is used to detect the dynamic pressure of the blade body under the excitation of the airflow generated by the movement of the excitation blade. A strain gauge is disposed on the surface of the blade and is used to detect the strain parameters of the blade under the action of the airflow.

[0007] In one exemplary embodiment of this disclosure, the cross-section of the excitation blade is a streamlined airfoil with a rounded leading edge and a tapering trailing edge.

[0008] In one exemplary embodiment of this disclosure, the drive structure includes a drive motor, a transmission shaft, and a crank-slider assembly; the output end of the drive motor is connected to the transmission shaft, and the transmission shaft is connected to the excitation blade via the crank-slider assembly to drive the excitation blade to perform linear reciprocating motion relative to the turbine blade along the first direction.

[0009] In one exemplary embodiment of this disclosure, the test apparatus further includes a mounting base and a guide rail. The mounting base is fixedly disposed on the slider of the crank-slider assembly, and the excitation blade is fixedly disposed on the mounting base. The guide rail is fixedly disposed relative to the first grid plate and extends along the first direction, and the slider of the crank-slider assembly is slidably disposed on the guide rail.

[0010] In an exemplary embodiment of this disclosure, the mounting base has a mounting square hole, and the end of the excitation blade is provided with a mounting square post. The mounting square hole and the mounting square post are inserted and engaged in a direction perpendicular to the surface of the first grid plate.

[0011] In an exemplary embodiment of this disclosure, both the first grid plate and the second grid plate are provided with a groove extending along the first direction; The mounting base is located on the side of the first grid plate away from the second grid plate and on the side of the second grid plate away from the first grid plate. The mounting post of the excitation blade passes through the slide groove and is inserted into the mounting hole on the mounting base.

[0012] In one exemplary embodiment of this disclosure, the crank, the slider, the mounting base, and the guide rail are symmetrically arranged on the side of the second grid plate away from the first grid plate.

[0013] In one exemplary embodiment of this disclosure, the test apparatus further includes a protective cover, which is fixedly disposed on the side of the first grid plate away from the second grid plate and on the side of the second grid plate away from the first grid plate. The crank, slider, mounting base and guide rail are all disposed inside the protective cover.

[0014] In one exemplary embodiment of this disclosure, the protrusion is provided with an air inlet and an air outlet, the air inlet being used to connect to an external heating medium, and the air outlet being used to discharge the heating medium; The blade body has an interconnected air inlet channel and an air outlet channel. The air inlet channel is connected to the air inlet hole, and the air outlet channel is connected to the air outlet hole. The heating medium can pass through the air inlet hole, the air inlet channel, and the air outlet channel in sequence, and be discharged from the air outlet hole.

[0015] According to one aspect of this disclosure, a test method for a multi-row turbine planar blade cascade with wake excitation is provided, comprising: performing a fluid-structure interaction test or a fluid-thermal-structure interaction test using the multi-row turbine planar blade cascade test apparatus with wake excitation described in any of the above embodiments.

[0016] The multi-row turbine planar blade test apparatus and method with wake excitation disclosed herein, by setting up excitation blades that can reciprocate relative to the turbine blades, can conduct tests with wake excitation, realizing a full-dimensional simulation of the fluid-structure interaction effect of turbine blades under actual working conditions. Compared with traditional static or single load tests, it has a higher degree of working condition reproduction and the test results are closer to engineering reality. It can provide more valuable test data and theoretical basis for the aerodynamic design, structural strength verification and fatigue life assessment of aero-engine turbine blades.

[0017] It should be understood that the above general description and the following detailed description are exemplary and explanatory only, and are not intended to limit this disclosure. Attached Figure Description

[0018] The accompanying drawings, which are incorporated in and form part of this specification, illustrate embodiments consistent with this disclosure and, together with the description, serve to explain the principles of this disclosure. It is obvious that the drawings described below are merely some embodiments of this disclosure, and those skilled in the art can obtain other drawings based on these drawings without any inventive effort.

[0019] Figure 1 This is a schematic diagram of the structure of a multi-row turbine planar blade cascade test device with wake excitation in one embodiment of the present disclosure; Figure 2 This is a top view of a test apparatus for a multi-row turbine planar blade cascade with wake excitation according to an embodiment of the present disclosure; Figure 3 for Figure 2 Cross-sectional view at the PP section; Figure 4 This is a top view of the first grid plate in one embodiment of the present disclosure; Figure 5 This is a top view of the second grid plate in one embodiment of the present disclosure; Figure 6 This is a schematic diagram of the structure of the excitation blade in one embodiment of the present disclosure; Figure 7 This is a schematic diagram of the structure of a turbine blade in one embodiment of the present disclosure; Figure 8 When the first via is located near the second surface in one embodiment of this disclosure Figure 7 Sectional view at point AA; Figure 9 When the first via is provided near the first surface in one embodiment of this disclosure Figure 7 Sectional view at point AA; Figure 10 This is a top view of the boss in one embodiment of the present disclosure; Figure 11 This is a schematic diagram of a turbine blade assembled on a first grid plate according to an embodiment of the present disclosure; Figure 12 This is a schematic diagram of a slider assembled on a guide rail in one embodiment of the present disclosure; Figure 13 This is a schematic diagram of a guide rail in one embodiment of the present disclosure; Figure 14 This is a schematic diagram of a slider in one embodiment of the present disclosure; Figure 15 This is a schematic diagram of a transmission rod in one embodiment of the present disclosure; Figure 16 This is a schematic diagram of a crank in one embodiment of the present disclosure; Figure 17 This is a schematic diagram of a mounting base according to one embodiment of the present disclosure; Figure 18 This is a schematic diagram of a protective cover according to one embodiment of the present disclosure; Figure 19 This is a schematic diagram from another perspective of the protective shield in one embodiment of the present disclosure; Figure 20 This is a schematic diagram of a spacer rod in one embodiment of the present disclosure; Figure 21 This is a schematic diagram of the first isolation member in one embodiment of the present disclosure; Figure 22 This is a schematic diagram of the second isolation member in one embodiment of the present disclosure; Figure 23 Strain in three directions (0°, 45°, and 90°) in one embodiment of this disclosure , .

[0020] Explanation of reference numerals in the attached figures: 1- Test apparatus for multi-row turbine planar blade cascade with wake excitation; 11-First grid plate; 11a-Fixing threaded hole; 11b-Pressure measuring hole; 11c-Wire passage hole; 111-Slide groove; 112-Card interface; 12-Turbine blade; 121-Boss; 121a-Inlet; 121b-Outlet; 121c-Boss fixing threaded hole; 1212-First through hole; 1213-Second through hole; 122 - Blade body; 122a - First surface; 122b - Second surface; 1221 - Inlet passage; 1222 - Outlet passage; 1223 - First through hole; 1224 - Second through hole; 13-Second grid plate; 14-Excitation blade; 141-Mounting column; 151 - Drive motor; 152 - Drive shaft; 152a - Connecting section; 152b - Pin; 152c - Drive shaft through hole; 153-Crank-slider assembly; 1531-Crank; 1532-Slider; 1532a-Second threaded hole; 16-Guide groove; 16a-Interlocking protrusion; 17-Strain gauge; 18-Mounting base; 181-Mounting square hole; 182-First threaded hole; 183-Hinge post; 19-Guide rail; 191-Third threaded hole; 192-Intercepting slot; 20 - Protective cover; 20a - Protective cover fixing threaded hole; 201 - Fourth threaded hole; 21-Spacer rod; 211-Telescopic part; 212-Fixing part; 21a-Spacer rod mounting hole; 22-Handle; 23-First isolation element; 24 - Second isolation piece. Detailed Implementation

[0021] Exemplary embodiments will now be described more fully with reference to the accompanying drawings. However, these exemplary embodiments can be implemented in many forms and should not be construed as limited to the embodiments set forth herein; rather, they are provided so that this disclosure will be thorough and complete, and will fully convey the concept of the exemplary embodiments to those skilled in the art. The same reference numerals in the drawings denote the same or similar structures, and therefore detailed descriptions of them will be omitted. Furthermore, the drawings are merely illustrative of this disclosure and are not necessarily drawn to scale.

[0022] Although relative terms such as "up" and "down" are used in this specification to describe the relative relationship of one component of an icon to another, these terms are used only for convenience, such as according to the orientation of the examples shown in the accompanying drawings. It is understood that if the device of the icon is flipped upside down, the component described as "up" will become the component described as "down." When a structure is "up" of another structure, it may mean that the structure is integrally formed on the other structure, or that the structure is "directly" mounted on the other structure, or that the structure is "indirectly" mounted on the other structure through another structure.

[0023] The terms “a,” “one,” “the,” “the,” and “at least one” are used to indicate the presence of one or more elements / components / etc.; the terms “including” and “having” are used to indicate an open-ended inclusion and to mean that there may be other elements / components / etc. in addition to the listed elements / components / etc.; the terms “first” and “second” are used only as markers and are not a limitation on the number of objects.

[0024] The following will describe specific embodiments and appendices. Figure 1-23 The technical solution of the test device and method for multi-row turbine planar blade cascade with wake excitation in this application is further described.

[0025] like Figures 1 to 11 As shown, the multi-row turbine planar blade test device 1 with wake excitation disclosed herein includes: a first grid plate 11, a turbine blade 12, a second grid plate 13, an excitation blade 14, a drive structure, a pressure testing assembly, and strain gauges 17; the turbine blade 12 includes an integrally formed boss 121 and a blade body 122, the boss 121 being detachably connected to the first grid plate 11; the second grid plate 13 is located on the side of the blade body 122 away from the first grid plate 11 and is connected to the first grid plate 11, with a gap between the second grid plate 13 and the end of the blade body 122 away from the boss 121; the excitation blade 14 is located on the first... A grid plate 11 and a second grid plate 13 are positioned between each other and can reciprocate along a first direction, which is parallel to the length direction of the first grid plate 11. A driving structure is used to drive the excitation blade 14 to reciprocate along the first direction. A pressure testing assembly is disposed within the blade body 122. When the excitation blade 14 reciprocates relative to the turbine blade 12 along the first direction, the pressure testing assembly is used to detect the dynamic pressure of the blade body 122 under the excitation of the airflow generated by the movement of the excitation blade 14. A strain gauge 17 is disposed on the surface of the blade body 122 and is used to detect the strain parameters of the blade body 122 under the action of the airflow. The first direction is... Figure 1 The direction indicated by the middle arrow X.

[0026] In the experimental device 1 of the present invention, a multi-row turbine planar blade cascade with wake excitation is driven by a drive structure to reciprocate relative to the turbine blade 12 along a first direction parallel to the surface of the first cascade plate 11. During the movement, the excitation blade 14 periodically sweeps across the flow field region in front of the turbine blade 12, forming periodic disturbances and wake excitations on the airflow around the turbine blade 12, thereby simulating the wake flow field characteristics generated when a rotating blade sweeps past a stationary blade in a real turbine structure. This periodic airflow excitation acts on the surface of the blade body 122, causing different positions of the blade body 122 to bear aerodynamic loads that change with time.

[0027] Since the boss 121 of the turbine blade 12 is fixed to the first grid plate 11, the end of the blade 122 away from the boss 121 is a free end. The blade 122 is deformed under the repeated action of the periodic airflow. At the same time, the deformed blade 122 will in turn affect the flow field distribution on its surface, thus forming a typical fluid-structure interaction, which can truly simulate the actual working process of the turbine blade 12.

[0028] In this process, the dynamic pressure on the surface of the blade 122 is detected by a pressure testing component installed inside the blade 122, and the strain parameters of the blade 122 are detected by a strain gauge 17 installed on the surface of the blade 122. Based on the dynamic pressure and strain parameters, the fluid-structure interaction law on the blade 122 is analyzed, providing theoretical support for the design and development of aero-engine blades.

[0029] In summary, this multi-row turbine planar blade test device 1 with wake excitation, by setting up excitation blades 14 that can reciprocate relative to the turbine blades 12, reproduces the wake excitation condition of the turbine, and realizes a full-dimensional simulation of the fluid-structure interaction effect of the turbine blades 12 under actual working conditions. Compared with traditional static or single load tests, it has a higher degree of condition reproduction and the test results are closer to engineering reality. It can provide more valuable test data and theoretical basis for the aerodynamic design, structural strength verification and fatigue life assessment of aero-engine turbine blades 12.

[0030] In this embodiment, the first grid plate 11 can be a flat plate structure. The first grid plate 11 can be connected to the test bench, and its size corresponds to the size of the test bench. For example, the outer area of ​​the first grid plate 11 can be provided with multiple fixing threaded holes 11a that respectively mate with multiple mounting holes on the test bench. The fixing threaded holes 11a can be through holes, and screws or bolts can be passed through the fixing threaded holes 11a and the mounting holes on the test bench to detachably connect the first grid plate 11 to the test bench. In addition, a row of pressure measuring holes 11b is provided on each of the upper and lower sides of the first grid plate 11, which are used to measure the pressure at the leading edge of the excitation blade 14 and the pressure at the trailing edge of the turbine blade 12, respectively.

[0031] In some embodiments of this disclosure, the cross-section of the excitation blade 14 is a streamlined airfoil with a rounded leading edge and a tapering trailing edge.

[0032] The use of this airfoil structure enables the excitation blade 14 to more closely resemble the aerodynamic shape of the real turbine blade 12 during reciprocating motion, thereby maximally replicating the flow field environment under real working conditions and improving the authenticity and reliability of the test results.

[0033] Compared to the use of non-airfoil structures such as round bars to simulate upstream blades in related experimental models, this experiment uses an excitation blade 14 with real airfoil characteristics. Before the experiment, multi-dimensional scheme optimization can be completed through numerical simulation methods. For example, the airfoil type can be determined and the leading edge and trailing edge dimensions of the airfoil can be modified to maximize the wake excitation effect. The relative position of the wake excitation structure and the turbine blade 12 can be determined through numerical simulation to accurately simulate the rotation-to-stationary interference effect. At the same time, based on the numerical analysis results, key experimental conditions such as experimental frequency and Mach number can be determined to ensure the rationality of the experimental conditions.

[0034] For example, the excitation blade 14 section can adopt a NACA airfoil. The NACA airfoil is a streamlined shape with a rounded leading edge and a sharp trailing edge. The upper and lower contours of the symmetrical airfoil are symmetrically distributed, while the asymmetrical airfoil has a certain curvature and the whole is smoothly transitioned along the chord direction.

[0035] In some embodiments of this disclosure, such as Figure 3 , Figures 12 to 17 As shown, the drive structure includes a drive motor 151, a transmission shaft 152, and a crank-slider assembly 153. The output end of the drive motor 151 is connected to the transmission shaft 152, and the transmission shaft 152 is connected to the excitation blade 14 through the crank-slider assembly 153 to drive the excitation blade 14 to perform linear reciprocating motion relative to the turbine blade 12 in a first direction.

[0036] In this embodiment, the multi-row turbine planar blade test device 1 with wake excitation operates by having the drive motor 151 output continuous rotational power, which is synchronously transmitted to the crank-slider assembly 153 via the transmission shaft 152. The crank-slider assembly 153 converts the rotational motion of the transmission shaft 152 into linear reciprocating motion along a first direction, thereby driving the excitation blades 14 to perform periodic reciprocating motion at a set frequency and stable stroke. This allows the excitation blades 14 to continuously and regularly sweep across the flow field in front of the turbine blades 12, thereby forming a periodic wake excitation with stable frequency and uniform intensity. In this embodiment, the excitation frequency can be flexibly adjusted by adjusting the speed of the drive motor 151, which can simulate the wake excitation conditions of a real turbine at different speeds, further improving the accuracy of the test in replicating the real working environment.

[0037] Of course, the drive structure in this disclosure is not limited to the above form. For example, the drive structure can also adopt a linear motor direct drive structure, specifically including a linear motor and its mover assembly. The mover is directly connected to the excitation blade 14, and the linear motor directly drives the excitation blade 14 to perform linear reciprocating motion along the first direction.

[0038] It is worth noting that the other end of the crank 1531 can be directly connected to the slider 1532 or indirectly connected to the slider 1532. The following describes in detail an embodiment where the other end of the crank 1531 is indirectly connected to the slider 1532. In some embodiments of this disclosure, such as... Figures 12 to 17 As shown, the multi-row turbine planar blade test device 1 with wake excitation also includes a mounting base 18 and a guide rail 19. The mounting base 18 is fixed on the slider 1532 of the crank slider assembly 153, and the excitation blade 14 is fixed on the mounting base 18. The guide rail 19 is fixedly disposed relative to the first grid plate 11 and extends along the first direction.

[0039] In this embodiment, the two ends of the crank 1531 are connected to the mounting base 18 and the drive shaft 152, respectively. The hinge pin 183 of the mounting base 18 is fitted into the mounting hole at one end of the crank 1531, and the drive shaft 152 is fitted into the mounting hole at the other end of the crank 1531. Thus, when the drive shaft 152 rotates, the crank 1531 can drive the mounting base 18 to move synchronously. A mounting base 18 is arranged on each of the left and right sides of the first grid plate 11. Each end of the mounting base 18 is provided with several screw holes for connecting to the slider 1532, so that the mounting base... The 18 can achieve stable linear reciprocating motion along the guide rail 19. Thus, when the multi-row turbine planar blade test device 1 with wake excitation is working, the crank 1531 slider 1532 mechanism drives the slider 1532 to make linear reciprocating motion along the guide rail 19. The slider 1532 drives the mounting base 18 and the excitation blade 14 to move synchronously. This can effectively prevent the slider 1532 and the excitation blade 14 from lateral deviation, swaying or wobbling during the movement, ensuring that the movement trajectory of the excitation blade 14 is accurate and consistent, thereby forming a stable and regular periodic wake excitation in front of the turbine blade 12.

[0040] Specifically, the mounting base 18 has a plurality of first threaded holes 182 along the thickness direction, and the slider 1532 has corresponding second threaded holes 1532a that are coaxially aligned with each of the first threaded holes 182. During assembly, the bolts are sequentially inserted into the second threaded holes 1532a of the slider 1532 and the first threaded holes 182 of the mounting base 18 and tightened to achieve a detachable rigid connection between the mounting base 18 and the slider 1532, ensuring that the two move completely synchronously without relative displacement. The connecting section 152a of the transmission rod is inserted into the drive end of the drive motor 151, and a pin 152b is fitted at its end. The two ends of the crank 1531 are respectively provided with a first connecting hole 1531a and a second connecting hole 1531b. The pin 152b at the end of the transmission rod is rotatably inserted into the first connecting hole 1531a of the crank 1531. The mounting base 18 is also provided with a screw that is hinged to the second connecting hole 1531b of the crank 1531. In this way, the rotational power output by the drive motor 151 is transmitted to the mounting base 18 and the slider 1532 in sequence through the transmission rod and the crank 1531, driving the two to make reciprocating linear motion along the guide rail 19.

[0041] Among them, such as Figures 12 to 14 As shown, the slider 1532 and the guide rail 19 adopt a fitted sliding guide fit structure: the slider 1532 has a guide groove 16 on the side facing the guide rail 19 that matches the shape of the guide rail 19. The groove wall of the guide groove 16 is provided with an insertion protrusion 16a. The upper and lower sides of the guide rail 19 each have an insertion groove 192 corresponding to the insertion protrusion 16a. The guide rail 19 is inserted into the guide groove 16 of the slider 1532 along the first direction, forming a tightly fitted sliding pair. During the test, the slider 1532 moves smoothly along the first direction under the drive of the crank 1531 slider 1532 mechanism, relying on the fit constraint of the guide groove 16 and the guide rail 19. This fitting can form an all-round lateral and normal limit for the slider 1532, effectively preventing the slider 1532 from shaking, deviating or flipping during high-frequency reciprocating motion, and further ensuring the accuracy and consistency of the motion trajectory of the excitation blade 14.

[0042] In some embodiments of this disclosure, such as Figure 16 As shown, the mounting base 18 has a mounting square hole 181, and the end of the excitation blade 14 is provided with a mounting square post 141. The mounting square hole 181 and the mounting square post 141 are inserted and engaged in a direction perpendicular to the surface of the first grid plate 11.

[0043] In this way, the circumferential limiting effect of the mounting square hole 181 and the mounting square post 141 can be used to prevent the excitation blade 14 from rotating or deflecting circumferentially during the reciprocating motion of the mounting base 18, thereby ensuring the stability of the attitude of the excitation blade 14 and ensuring that it always acts on the flow field at a set angle, ensuring that the wake excitation is regular and uniform, thus ensuring the continuous and stable test process and accurate and reliable test data. In addition, the plug-in connection method is simple and quick to disassemble and assemble, and reliable positioning can be achieved without complex fasteners. It is convenient to quickly replace different models of excitation blades 14 according to test requirements, thereby improving the adaptability and operating efficiency of the multi-row turbine planar blade cascade test device 1 with wake excitation.

[0044] Of course, in other embodiments of this disclosure, in addition to the square plug-in structure, other structural forms can be used to prevent the excitation blade 14 from rotating or deflecting circumferentially during reciprocating motion. For example, a D-shaped hole is opened on the mounting base 18, and a matching D-shaped shaft is provided at the end of the excitation blade 14. Circumferential anti-rotation is achieved by limiting the non-circularity of the D-shaped section. Alternatively, a flat keyway is opened on the mounting shaft of the excitation blade 14, and a corresponding keyway is provided in the mounting hole of the mounting base 18. Transmission and anti-rotation are achieved by embedding the flat key into the keyways on both sides.

[0045] In some embodiments of this disclosure, such as Figure 4 As shown, both the first grid plate 11 and the second grid plate 13 are provided with a sliding groove 111 extending along the first direction; the mounting base 18 is located on the side of the first grid plate 11 away from the second grid plate 13 and on the side of the second grid plate 13 away from the first grid plate 11. The mounting square post 141 of the excitation blade 14 passes through the sliding groove 111 and is inserted into the mounting square hole 181 on the mounting base 18.

[0046] Thus, the groove 111 extends along the direction of movement of the excitation blade 14, providing space for the mounting column 141 to move and forming a lateral constraint on the mounting column 141 during movement, further limiting the lateral offset and sway of the excitation blade 14. Combined with the square plug-in anti-rotation structure of the mounting column 141 and the mounting square hole 181, it can doubly ensure that the excitation blade 14 does not rotate or deflect in the high-frequency reciprocating motion, making its motion posture stable and its trajectory consistent, thereby ensuring that the wake excitation is uniform and controllable, and improving the accuracy of flow field simulation and the stability of experimental data.

[0047] Furthermore, by arranging the mounting base 18 outside the first grid plate 11 and the second grid plate 13, the drive and transmission structure can be separated from the internal flow field area, avoiding interference of the transmission components with the test airflow, ensuring the purity of the flow field, and reducing the impact of additional airflow disturbance on the test results.

[0048] In some embodiments of this disclosure, such as Figures 1 to 3As shown, the second grid plate 13 is symmetrically provided with a crank 1531, a slider 1532, a mounting base 18 and a guide rail 19 on the side away from the first grid plate 11.

[0049] Thus, the two ends of the excitation blade 14 are connected to the mounting bases 18 on both sides respectively, and the two ends are driven synchronously by the same drive shaft 152. This allows the excitation blade 14 to be subjected to balanced force and move synchronously during reciprocating motion, avoiding end swaying, twisting or motion lag caused by unilateral drive, ensuring that the excitation blade 14 moves smoothly and linearly along the first direction, and further improving the uniformity of wake excitation and the accuracy of flow field simulation.

[0050] Furthermore, in this embodiment, such as Figures 1 to 3 , Figure 21 , Figure 22 As shown, a first isolator 23 can be bolted to the first grid plate 11 to the connection part of the drive motor 151, the drive shaft 152 and the crank 1531. A second isolator 24 is bolted to the second grid plate 13 to protect the connection part of the drive shaft 152 and the crank 1531. The first isolator 23 and the second grid plate 13 can also be provided with a drive shaft through hole 152c for the connection section 152a of the drive shaft 152 to pass through, a slide groove 111 for the square column of the excitation blade 14 to pass through, and a protective cover fixing threaded hole 20a. Optionally, a row of pressure measuring holes 11b can be provided on the upper and lower sides of the second grid plate 13 to measure the pressure at the leading edge of the excitation blade 14 and the pressure at the trailing edge of the turbine blade 12, respectively.

[0051] In some embodiments of this disclosure, such as Figure 1 , Figures 17 to 19 As shown, the multi-row turbine planar blade cascade test device 1 with wake excitation also includes a protective cover 20. The protective cover 20 is fixedly disposed on the side of the first cascade plate 11 away from the second cascade plate 13, and on the side of the second cascade plate 13 away from the first cascade plate 11. The crank-slider assembly 153, the mounting base 18, and the guide rail 19 are all disposed inside the protective cover 20. Screw holes are provided on both the protective cover 20 and the first cascade plate 11, and the protective cover 20 can be fixed to the first cascade plate 11 and the second cascade plate 13 by bolts. The first grid plate 11 and the protective cover 20 are provided with a plurality of protective cover fixing threaded holes 20a, so that the protective cover 20 can be fixed to the first grid plate 11 by bolts. The guide rail 19 is provided with a plurality of third threaded holes 191, and the side wall of the protective cover 20 is provided with a fourth threaded hole 201 that is coaxial with each of the third threaded holes 191. During assembly, the bolts are sequentially inserted into the third threaded holes 191 of the guide rail 19 and the fourth threaded holes 201 of the first grid plate 11 and tightened to achieve a detachable rigid connection between the guide rail 19 and the protective cover 20, ensuring the accuracy of the installation position and the structural stability of the guide rail 19. The connection between the second grid plate 13 and the protective cover 20 is the same as described above, and will not be described again here.

[0052] The protective cover 20 is fixedly installed on the side of the first grid plate 11 away from the second grid plate 13, and on the side of the second grid plate 13 away from the first grid plate 11. The crank-slider assembly 153, the mounting base 18, and the guide rail 19 are all located inside the protective cover 20. This effectively isolates the motion transmission components from the external environment and the test flow field area. On the one hand, it prevents dust and impurities from entering the gap between the guide rail 19 and the slider 1532 or the transmission part between the crank 1531 and the slider 1532, reducing component wear and motion jamming, and improving the operational stability and service life of the transmission mechanism. On the other hand, it prevents the high-speed reciprocating motion of the components during the test from causing safety hazards to the operators, improving the safety of the multi-row turbine planar blade test device 1 with wake excitation. At the same time, the protective cover 20 can block the airflow disturbance generated during the movement of the transmission mechanism, preventing it from interfering with the test flow field near the turbine blades 12, ensuring a pure and stable flow field, thereby improving the accuracy of pressure and strain test data. In addition, the protective cover 20 can also reduce the operating noise of the mechanism, optimize the test environment, and improve the overall reliability, safety, and testing accuracy of the device.

[0053] In some embodiments of this disclosure, such as Figure 10 As shown, the boss 121 has an air inlet 121a and an air outlet 121b. The air inlet 121a is used to connect to the external heating medium, and the air outlet 121b is used to discharge the heating medium. The blade body 122 has an interconnected air inlet channel 1221 and an air outlet channel 1222. The air inlet channel 1221 is connected to the air inlet 121a, and the air outlet channel 1222 is connected to the air outlet 121b. The heating medium can pass through the air inlet 121a, the air inlet channel 1221, and the air outlet channel 1222 in sequence, and be discharged from the air outlet 121b.

[0054] Thus, by setting a through-flow heat flow channel inside the blade and setting inlet and outlet interfaces at the boss 121, the external heating medium can be directly introduced into the blade for circulating heat exchange, so that the blade as a whole is heated uniformly. This realistically simulates the high-temperature environment faced by the turbine blade 12 in actual operation of the aero-engine. This built-in channel structure does not damage the external aerodynamic shape of the blade and will not cause additional interference to the flow field. It can reproduce high-temperature conditions while conducting aeroelastic and fluid-structure interaction tests, making the test conditions closer to the actual service conditions. Moreover, the circulation path of the heating medium is closed and controllable, which makes it easy to adjust the temperature and flow rate, realize the simulation of temperature field under different operating conditions, effectively improve the comprehensiveness and simulation degree of the test, and provide reliable conditions for the study of the structural deformation, stress distribution and aerodynamic characteristics of the blade under high-temperature conditions.

[0055] In some embodiments of this disclosure, please continue to refer to the corresponding figures. A card interface 112 is provided on the first grid plate 11, and the card interface 112 can penetrate the first grid plate 11 through its thickness direction. The shape of the card interface 112 matches the shape of the outer peripheral surface of the blade 122, and the card interface 112 can be used to assemble the blade 122. For example, the shape of the card interface 112 is the same as the shape of the outer peripheral surface of the blade 122, and the size of the card interface 112 can be slightly larger than the size of the outer peripheral surface of the blade 122. The end of the blade 122 near the boss 121 can pass through the card interface 112. In this case, the surface of the boss 121 near the blade 122 can contact the first grid plate 11. The number of card interfaces 112 can be multiple, and the multiple card interfaces 112 can be distributed at intervals along the length direction of the first grid plate 11. For example, the number of card interfaces 112 can be 2, 4, 6, 8, 10, 12 or more. Of course, other numbers are also possible, which will not be listed here.

[0056] As shown in the corresponding attached figures, the boss 121 may be block-shaped and detachably connected to the first grid plate 11 to prevent the blades from being vibrated and falling off during the fluid-structure interaction test. For example, the boss 121 may be provided with multiple spaced-apart boss fixing threaded holes 121c, and correspondingly, the first grid plate 11 may be provided with multiple spaced-apart boss fixing threaded holes 121c. Please continue to refer to the corresponding attached figures. The multi-row turbine planar blade cascade test device 1 with wake excitation disclosed herein may also include multiple fasteners. The fasteners may be strip-shaped and may be threaded. Each fastener can be fastened by passing through the corresponding distributed boss fixing threaded holes 121c. For example, the fasteners may be screws or bolts.

[0057] As shown in the attached figure, the second grid plate 13 can be a flat plate structure, and its dimensions must correspond to the installation dimensions of the test bench to ensure that there is no gap between the second grid plate and the test bench, so as to prevent air leakage at the gap from affecting the flow field. Please continue to refer to the attached figure. The second grid plate 13 can be located on the side of the blade 122 away from the first grid plate 11, and the second grid plate 13 can be connected to the first grid plate 11.

[0058] In one exemplary embodiment of this disclosure, the second grid plate 13 and the end of the blade 122 away from the boss 121 have a gap, which may be approximately 0.5 mm. That is, there is no contact between the second grid plate 13 and the blade 122, and the end of the blade 122 away from the first grid plate 11 is a free end. In other words, the blade in this disclosure is a blade similar to a cantilever beam.

[0059] In one exemplary embodiment of this disclosure, as shown in the corresponding figures, the multi-row turbine planar blade test device 1 with wake excitation of this disclosure may further include two spacer rods 21, which can be used to fix the second grating plate 13 and the first grating plate 11 together. The two spacer rods 21 may be respectively disposed on both sides of the blade body 122. The spacer rods 21 may be rod-shaped, and their cross-section may be circular. Both spacer rods 21 may be connected between the first grating plate 11 and the second grating plate 13.

[0060] In some embodiments of this disclosure, such as Figure 20 The spacer rod 21 is telescopic, and the distance between the first grid plate 11 and the second grid plate 13 can be adjusted by adjusting the length of the spacer rod 21, so as to test blades of different lengths. This helps to improve the applicability of the multi-row turbine planar blade test device 1 with wake excitation disclosed herein and reduce test costs.

[0061] In some embodiments of this disclosure, please continue to refer to the corresponding drawings. The spacer 21 may include a telescopic part 211 and a fixing part 212 respectively connected to both sides of the telescopic part 211. The telescopic part 211 may be cylindrical and may have threads inside, that is, the telescopic part 211 may be a threaded cylinder. The fixing part 212 may be rod-shaped and have external threads at both ends. The first grid plate 11 may have two spacer mounting holes 21a. At the same time, the second grid plate 13 may have two corresponding spacer mounting holes 21a. The end of the fixing part 212 of the spacer 21 that is close to the first grid plate 11 and away from the telescopic part 211 may pass through the spacer mounting hole 21a. The end of the fixing part 212 of the spacer 21 that is close to the second grid plate 13 and away from the telescopic part 211 may also pass through the spacer mounting hole 21a. A first nut can be provided on the side of the first grid plate 11 away from the spacer rod 21, and the first nut can be threadedly connected to the end of the fixing part 212 passing through the first grid plate 11; a second nut (not shown in the figure) can be provided on the side of the second grid plate 13 away from the spacer rod 21, and the second nut can be threadedly connected to the end of the fixing part 212 passing through the second grid plate 13. The distance between the first grid plate 11 and the second grid plate 13 can be adjusted by rotating the telescopic part 211 to accommodate blades of different lengths.

[0062] The pressure testing assembly can be installed inside the blade 122, and can be used to detect the dynamic pressure of the blade under the action of the test airflow. For example, the pressure testing assembly can be installed in a region of the blade 122 with good aerodynamic performance, and the specific location of this region can be obtained through simulation.

[0063] In one exemplary embodiment of this disclosure, please continue to refer to the corresponding drawings. The boss 121 may have a first through hole 1212 extending through the boss 121 along its thickness direction. The first through hole 1212 may be a straight hole, and the number of first through holes 1212 may be one or more, without special limitation. The cross-section of the first through hole 1212 may be circular, elliptical, rectangular, polygonal, or irregular in shape, without special limitation.

[0064] Please refer to the corresponding attached figures. The blade 122 may have a first through-hole 1223 and a second through-hole 1224 that communicate with each other. The first through-hole 1223 can pass through the blade 122 and extend along the length of the blade 122. The end of the first through-hole 1223 away from the second through-hole 1224 can communicate with a first through-hole 1212. The second through-hole 1224 extends in a different direction than the first through-hole 1223, and its opening is located on the surface of the blade 122. The cross-section of the first through-hole 1223 can be circular, elliptical, rectangular, polygonal, or irregular in shape, without special limitation. The shape of the cross-section of the second through-hole 1224 can be the same as or different from the shape of the cross-section of the first through-hole 1223, without special limitation.

[0065] During the experiment, under the action of the detected airflow, the first surface 122a of the blade 122 can serve as the suction surface, and the second surface 122b can serve as the pressure surface. In some embodiments of this disclosure, as shown in the corresponding figures, the second through hole 1224 can be disposed close to the first surface 122a of the blade 122, that is, it can be disposed close to the suction surface of the blade 122. In other embodiments of this disclosure, as shown in the corresponding figures, the second through hole 1224 is disposed close to the second surface 122b, that is, it can be disposed close to the pressure surface of the blade 122.

[0066] In one exemplary embodiment of this disclosure, the position of the second via 1224 can be a region in the blade 122 with better aerodynamic performance. This position can be obtained through simulation. For example, in some embodiments of this disclosure, simulations have shown that the aerodynamic performance of the blade 122 is best at a position where the distance from the boss 121 to the blade 122 is three-quarters of the length of the blade 122. Therefore, the position of the second via 1224 can be set at a position in the blade 122 where the distance from the boss 121 to the blade 122 is three-quarters of the length of the blade 122.

[0067] In one exemplary embodiment of this disclosure, the pressure testing assembly may include a conduit inserted into a first through hole 1212. A first through hole 1223 is interconnected with the outside of the blade body 122. The first through hole 1212, the conduit, and the first through hole 1223 form an interconnected fluid channel. Within the interconnected fluid channel, the pressure of the same fluid can be transmitted equivalently. Therefore, the pressure at the first through hole 1223 on the surface of the blade body 122 can be extracted and measured through the conduit. This avoids structural interference and flow field disturbance caused by arranging test elements in a narrow through hole, while facilitating pressure extraction and detection, simplifying assembly and disassembly, and improving measurement stability.

[0068] As shown in the attached figure, strain gauge 17 can be disposed on the surface of blade 122, and the dynamic strain parameters of blade 122 under the action of the detection airflow can be detected in real time through strain gauge 17. The strain gauge 17 in this disclosure can be a three-flower strain gauge 17, which can be fixed to the surface of blade 122 by means of bonding, etc. Of course, other methods can also be used to fix the strain gauge 17 to the surface of blade 122; no special limitation is made here on the fixing method between strain gauge 17 and blade 122. The bonding position of strain gauge 17 can be determined based on the numerical simulation of the structural strength of blade 122. This bonding position is a region with a small stress gradient change near the location of the maximum stress in blade 122. For example, determining the bonding position of strain gauge 17 may include: determining the location of the critical point with the maximum stress in blade 122 based on the numerical simulation of the structural strength of blade 122; selecting a region with a small stress gradient change near the critical point; selecting four points (each with a stress gradient change of less than 5%) within this region to form a square area; and finally bonding strain gauge 17 to the center of this square area.

[0069] In this disclosure, strain gauges 17 can be attached to the center of the aforementioned square area to facilitate the acquisition of dynamic strain in three directions: axial 0°, spanwise 90°, and 45° with respect to the spanwise direction of the blade 122. To ensure the quality of the measured test data, strain gauges 17 can be attached to all blades 122 on the first grid plate 11 simultaneously to prevent one or more strain gauges 17 from falling off during the test due to the influence of the detection airflow, thus preventing the corresponding data from being detected. In this disclosure, each strain gauge 17 can be numbered to allow for data monitoring of each blade 122 individually.

[0070] In an exemplary embodiment of this disclosure, the boss 121 may also have a second through hole 1213 extending through the boss 121 along the thickness direction of the boss 121. The second through hole 1213 may be a straight hole, and the cross-section of the second through hole 1213 may be circular, elliptical, rectangular, polygonal or irregular in shape, without any special limitation. The second lead wire can pass through the second through hole 1213.

[0071] To reduce the interference of the strain gauge 17 measuring device on the airflow field on the blade surface 122, the multi-row turbine planar blade test device 1 with wake excitation disclosed herein may further include a second lead wire through which the strain signal can be derived. The second lead wire may be a wire with signal transmission function. The second lead wire may pass through the second through hole 1213 and the recess and be attached to the surface of the blade 122. For example, the second lead wire may be connected to the strain gauge 17 on the surface of the blade 122, and the strain test signal detected by the strain gauge 17 may be transmitted to a signal collection device through the second lead wire.

[0072] Correspondingly, the first grid plate 11 may also be provided with a wire-passing hole 11c for passing through the first lead and the second lead.

[0073] In one exemplary embodiment of this disclosure, as shown in the accompanying drawings, the multi-row turbine planar blade test apparatus 1 with wake excitation of this disclosure may further include multiple handles 22. At least one handle 22 is provided on the surface of the first grating plate 11 away from the second grating plate 13 and on the surface of the second grating plate 13 away from the first grating plate 11, respectively. The handles 22 facilitate placing the first grating plate 11 and the second grating plate 13 on the test bench or removing them from the test bench. For example, the number of handles 22 may be two, with one handle 22 provided on each surface of the first grating plate 11 and the second grating plate 13; or, the number of handles 22 may be four, with two handles 22 provided on each surface of the first grating plate 11 and the second grating plate 13, wherein the handles 22 may be detachably connected to the first grating plate 11 and / or the second grating plate 13 by bolts.

[0074] The following describes the testing process using the multi-row turbine planar blade cascade test apparatus 1 with wake excitation disclosed in this invention: According to the machining drawings and machining requirements, inspect whether the machined turbine blade 12 and excitation blade 14 are qualified. At this time, focus on the cross-sectional shape of the excitation blade 14, the surface smoothness of the turbine blade 12, and the size of the second through hole 1224. Before the turbine blade 12 and excitation blade 14 are delivered, pre-assembly should be carried out to ensure smooth cooperation and operation between the various components.

[0075] After the turbine blades 12 and excitation blades 14 pass the acceptance test, pressure testing components and strain gauges 17 are installed on the blade body 122 of each turbine blade 12. Then, the blade body 122 is inserted into the first grid plate 11 through the card interface 112 of the first grid plate 11, and the boss 121 is fixed to the first grid plate 11. Then, the multi-row turbine planar blade cascade test device 1 with wake excitation is installed on the test section of the wind tunnel test platform.

[0076] Connect the pressure testing assembly and strain gauge 17 to the data acquisition device. To ensure the safety of the test, a pre-test is conducted before the formal test. During the pre-test, all systems are in working condition, and excitation and response signals are collected. Check whether the operation of each system is normal. Repeat the above debugging process to eliminate faults until the entire system is completely normal.

[0077] During the formal test: The operating conditions of the test wind tunnel platform were set to pre-defined environmental parameters. By adjusting the output parameters of the drive motor 151, the crank-slider assembly 153 was controlled to drive the excitation blade 14 to reciprocate along the first direction at a preset frequency. The motion of the excitation blade 14 created periodic turbulent airflow in the flow field in front of the turbine blade 12, simulating the wake and airflow excitation effect of a real turbine rotating blade sweeping past a stationary blade. Based on the monitoring data of the wind tunnel test platform, after the motion state of the excitation blade 14 stabilized and the periodic turbulence of the flow field became regular, the strain parameters and dynamic pressure of the blade body 122 were collected and measured. During the test, the rotational speed of the drive motor 151 could be adjusted to change the reciprocating frequency and speed of the excitation blade 14, and the test data under different motion conditions were recorded accordingly. After the test, the blade and measuring equipment were checked for any damage during the test. If any damage was found, it was promptly replaced and repaired. In addition, the dynamic strain parameters of the blade body 122 in the spanwise directions of 0°, 45°, and 90° were checked to ensure there were no abnormalities.

[0078] The strain in the 0°, 45°, and 90° directions was collected under the experimental conditions at a frequency of 0.5 Mach and 10 Hz. , ,like Figure 23 As shown, where Figure 23 In the diagram, 'a' corresponds to the 0° direction, 'b' to the 45° direction, and 'c' to the 90° direction. Test data from the stable section can be selected for post-processing. This post-processing specifically includes: performing Fourier decomposition on these strain data to obtain the vibration frequency and amplitude of the blade 122 under the corresponding operating conditions. For each strain measurement point, after Fourier decomposition, the strain amplitude values ​​in three directions can be obtained. Then, based on the derivation formula of the first principal stress, the first principal stress at the test measurement point is obtained. In the later process of actual blade design, the first principal stress in this disclosure can be referenced. That is, the first principal stress measured and calculated by the multi-row turbine planar blade cascade test device 1 with wake excitation in this disclosure can provide theoretical data support for the design of actual blades.

[0079] The derivation formula for the first principal stress in this disclosure is as follows:

[0080] in, Let E be the first principal stress, E be the elastic modulus, and µ be Poisson's ratio. , The strains were measured at 0°, 45°, and 90°, respectively.

[0081] In an exemplary embodiment of this disclosure, this disclosure also provides a test method for a multi-row turbine planar blade cascade with wake excitation. The method uses the multi-row turbine planar blade cascade test device 1 with wake excitation in any of the above embodiments to perform a fluid-structure interaction test or a fluid-thermal-structure interaction test. The specific details and experimental process have been described in the corresponding embodiments of the multi-row turbine planar blade cascade test device 1 with wake excitation, so they will not be repeated here.

[0082] Other embodiments of this disclosure will readily occur to those skilled in the art upon consideration of the specification and practice of the invention disclosed herein. This disclosure is intended to cover any variations, uses, or adaptations of this disclosure that follow the general principles of this disclosure and include common knowledge or customary techniques in the art not disclosed herein. The specification and examples are to be considered exemplary only, and the true scope and spirit of this disclosure are indicated by the appended claims.

Claims

1. A test apparatus for a multi-row turbine planar blade cascade with wake excitation, characterized in that, include: First grid plate; The turbine blade includes an integrally formed boss and blade body, wherein the boss is detachably connected to the first grid plate; The second grid plate is disposed on the side of the blade away from the first grid plate and is connected to the first grid plate. The second grid plate has a gap with the end of the blade away from the boss. The excitation blade is located between the first grid plate and the second grid plate, and can reciprocate along a first direction, which is parallel to the length direction of the first grid plate. A driving structure is provided for driving the excitation blade to reciprocate along the first direction. A pressure testing component is disposed inside the blade body. When the excitation blade reciprocates relative to the turbine blade along the first direction, the pressure testing component is used to detect the dynamic pressure of the blade body under the excitation of the airflow generated by the movement of the excitation blade. A strain gauge is disposed on the surface of the blade and is used to detect the strain parameters of the blade under the action of the airflow.

2. The test apparatus for multi-row turbine planar blade cascades with wake excitation according to claim 1, characterized in that, The cross-section of the excitation blade is a streamlined airfoil with a rounded leading edge and a tapering trailing edge.

3. The test apparatus for multi-row turbine planar blade cascades with wake excitation according to claim 1, characterized in that, The drive structure includes a drive motor, a transmission shaft, and a crank-slider assembly; the output end of the drive motor is connected to the transmission shaft, and the transmission shaft is connected to the excitation blade through the crank-slider assembly to drive the excitation blade to perform linear reciprocating motion relative to the turbine blade along the first direction.

4. The test apparatus for multi-row turbine planar blade cascades with wake excitation according to claim 3, characterized in that, The test apparatus further includes a mounting base and a guide rail. The mounting base is fixedly mounted on the slider of the crank-slider assembly, and the excitation blade is fixedly mounted on the mounting base. The guide rail is fixedly mounted relative to the first grid plate and extends along the first direction, and the slider of the crank-slider assembly is slidably mounted on the guide rail.

5. The test apparatus for multi-row turbine planar blade cascades with wake excitation according to claim 4, characterized in that, The mounting base has a mounting square hole, and the end of the excitation blade is provided with a mounting square post. The mounting square hole and the mounting square post are inserted and fitted together in a direction perpendicular to the surface of the first grid plate.

6. The test apparatus for a multi-row turbine planar blade cascade with wake excitation according to claim 5, characterized in that, Both the first grid plate and the second grid plate are provided with a sliding groove extending along the first direction; The mounting base is located on the side of the first grid plate away from the second grid plate and on the side of the second grid plate away from the first grid plate. The mounting post of the excitation blade passes through the slide groove and is inserted into the mounting hole on the mounting base.

7. The test apparatus for multi-row turbine planar blade cascade with wake excitation according to any one of claims 4-6, characterized in that, The crank, the slider, the mounting base, and the guide rail are symmetrically arranged on the side of the second grid plate away from the first grid plate.

8. The test apparatus for multi-row turbine planar blade cascades with wake excitation according to claim 7, characterized in that, The test apparatus also includes a protective cover, which is fixedly disposed on the side of the first grid plate away from the second grid plate and on the side of the second grid plate away from the first grid plate. The crank-slider assembly, the mounting base, and the guide rail are all disposed inside the protective cover.

9. The test apparatus for multi-row turbine planar blade cascade with wake excitation according to any one of claims 1-7, characterized in that, The protrusion is provided with an air inlet and an air outlet. The air inlet is used to connect to an external heating medium, and the air outlet is used to discharge the heating medium. The blade body has an interconnected air inlet channel and an air outlet channel. The air inlet channel is connected to the air inlet hole, and the air outlet channel is connected to the air outlet hole. The heating medium can pass through the air inlet hole, the air inlet channel, and the air outlet channel in sequence, and be discharged from the air outlet hole.

10. A test method for a multi-row turbine planar blade cascade with wake excitation, characterized in that, This includes using the multi-row turbine planar blade test apparatus with wake excitation as described in any one of claims 1-9 to conduct fluid-structure interaction tests or fluid-thermal-structure interaction tests.

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