Aero-engine blade vibration testing device

Abstract

The invention provides an aero-engine blade vibration testing device which structurally comprises a damping base, an assembling layer, a testing structure, limiting plates and an electric control panel, the testing structure is positioned at the upper end of the damping base through the assembling layer, and the limiting plates are installed on the left side and the right side of the testing structure and electrically control the testing structure through the carried electric control panel; after the test structure is further improved, the two groups of bearing structures and the parallel plate are symmetrically positioned through the vertical plate, and then the bearing structures can be vertically pressed down or ascended through the vertical spring at the lower end and the two vertical folding pieces, so that the distance between the bearing structures and the parallel plate is changed, and the effect of changing the width of the test cavity is achieved; therefore, excessive loss of air flow of the air injection structure caused by overlarge space of the test cavity to the edge can be effectively avoided, and meanwhile, the blade can be positioned by replacing the original multiple groups of locking structures according to the rebound effect, so that the stability of blade positioning test and the vibration test accuracy can be improved.

Description

Technical Field

[0001] The invention relates to the technical field of aero-engine blade detection, and more specifically to an aero-engine blade vibration test device. Background Art

[0002] Aircraft engine blades are key components in aircraft engines, mainly divided into fan blades, compressor blades and turbine blades. The blades complete the compression and expansion of gas in the engine and generate powerful power with the highest efficiency to propel the aircraft forward. Therefore, after the manufacture of aircraft engine blades, they need to be tested for quality and performance by vibration testing devices, so that the vibration frequency of the blades can be monitored to prevent the generation of faults, thereby improving the safety and reliability of the subsequent blades in actual use and improving the performance and efficiency of the engine; In summary, the inventors have found that the existing vibration testing devices mainly have the following defects: since the test chamber space of the current vibration testing device is relatively large, the blades need to be fixed in combination with multiple sets of locking structures when entering the test chamber, which will reflect the inconvenience of loading and fixing the test; at the same time, due to the large test chamber space, the simulated high-pressure airflow component of the device is very easy to diffuse in the surrounding area of ​​the test chamber when spraying, thereby reducing the intensity of the vibration test and reducing the overall comprehensiveness of the vibration test. Summary of the invention

[0003] The technical solution adopted by the present invention to achieve the technical purpose is: an aircraft engine blade vibration test device, whose structure includes: a shock-absorbing base, an assembly layer, a test structure, a limit plate, and an electric control panel. The upper end of the shock-absorbing base positions the test structure through the assembly layer and the limit plates are installed on the left and right sides of the test structure and the test structure is electrically controlled through the carried electric control panel.

[0004] As a further improvement of the present invention, the test structure is provided with a bearing structure, one end of the bearing structure is connected to the left and right sides of the middle and lower parts of the vertical plate and the other end is connected to the inner layer of the limit plate through a connecting block, the bearing structure is communicated with the parallel plate above and the distance between the parallel plate and the bearing structure forms a detection cavity, and a restraining body is arranged in the middle of the parallel plate, and jet structures are also included on the left and right sides thereof, and the restraining body and the jet structure are communicated with the surface layer of the bearing structure below.

[0005] As a further improvement of the present invention, the bearing structure is provided with an anti-deflection device, the center of the upper end of the anti-deflection device is connected to a vertical spring and the left and right sides include vertical folding rods, the upper ends of the vertical folding rods and the vertical springs are inserted and embedded in the lower end of the support block, the upper layer of the support block is also connected to a solid block, and the surface of the solid block is fixed with a vibration detection module, which is electrically connected to the electric control panel through the power-on block embedded in the internal circuit of the vertical plate through the side.

[0006] As a further improvement of the present invention, the two groups of bearing structures and parallel plates are symmetrically installed through the vertical plate of the test structure, the bearing structure overlaps with the surface of the shock-absorbing base through the lower end anti-deflection device, and then the height of the solid block of the support block is controlled by the vertical spring and the vertical folding rod. When the height of the solid block is adjusted, the distance from the parallel plate changes.

[0007] As a further improvement of the present invention, the shock-absorbing base is arranged with a shock-absorbing wall in the vertical plate of the test structure, and further carries a reinforcement plate and a shock-absorbing plug rod. The limit plates on the left and right sides of the test structure are both square in shape to determine the position of the electric control panel, and then the test structure is electrically controlled by the power-carrying circuit carried.

[0008] As a further improvement of the present invention, the bearing structures on the left and right sides of the vertical plate and the parallel plates are set in symmetrical positions and then are interlaced and fixedly connected by connecting blocks and limit plates. A gas compressor is carried inside the jet structure to simulate high-speed airflow to test the blades, and the restraining body is arranged in the middle of the parallel plates.

[0009] As a further improvement of the present invention, the vibration detection module is provided with a block on each of the left and right sides of the surface of the solid block to contact the two sides of the blade. The power-on block is in a raised shape and can be inserted into the vertical plate to be electrically connected to the electronic control panel. The vertical spring is arranged at the middle distance between the two groups of vertical folding rods. The bottom layer of the anti-deflection device is in a flat shape and overlaps with the surface of the shock-absorbing base.

[0010] As a further improvement of the present invention, the anti-deflection device is provided with a disassembly rod, which passes through the side center of the plug block and is embedded in the lower side of the vertical plate for fixed connection, so that the load-bearing plate on the plug block overlaps with the surface of the shock-absorbing base, and connecting block 1 and connecting block 2 are also provided on the upper end of the load-bearing plate.

[0011] As a further improvement of the present invention, the connecting block 1 and the connecting block 2 are both in the shape of a "concave" character and one connecting block is provided on each of the left and right sides of the surface of the load-bearing plate. Three plug blocks are provided at the lower end of the load-bearing plate and a straight rail is opened in the center of the side of the plug block to allow the disassembly rod to pass through.

[0012] As a further improvement of the present invention, an adsorption block is also provided at one end of the disassembly and assembly rod connected to the side of the vertical plate, the right center of the adsorption block is connected to the left part of the insertion rod and a plastic part is also provided in the connection area, the plastic part is arranged at the upper and lower ends of the adsorption block, and the upper and lower ends of the insertion rod are also connected to sliders and the sliders are matched with the plastic parts in spacing.

[0013] As a further improvement of the present invention, the slider is set in a symmetrical position on the upper and lower surfaces of the insertion rod, the insertion rod and the adsorption block form a "T" shape and the two groups of plastic parts are small "L" shapes to cover the upper and lower edges of the adsorption block.

[0014] As a further improvement of the present invention, the slider is set in a symmetrical position on the upper and lower surfaces of the insertion rod, the insertion rod and the adsorption block form a "T" shape and the two groups of plastic parts are small "L" shapes to cover the upper and lower edges of the adsorption block.

[0015] As a further improvement of the present invention, the positioning block is connected to the middle part of the parallel plate and crosses with the sliding rod. The width of the side protrusion at the lower end of the sliding rod is greater than the width of the lower end of the sliding rod and is restrained by the lower layer of the positioning block. The protective block is a rubber product and is completely covered by the lower layer of the sliding rod and the side protrusion through the embedding of the card block.

[0016] As a further improvement of the present invention, an auxiliary block is also provided in the contact area between the sliding rod and the internal positioning block. The upper end of the auxiliary block is connected to the lower end of the reinforcing block and a sliding layer is provided on the upper layer of the reinforcing block. A threaded groove is opened in the middle of the sliding layer, and the screw is locked through the threaded groove.

[0017] As a further improvement of the present invention, the auxiliary block and the reinforcing block are perpendicular to each other and a linear thread rail is opened in the center of the thread groove position area to match the screw rod.

[0018] Compared with the prior art, the present invention has the following beneficial effects: 1. The present invention is further improved on the test structure, and the two groups of bearing structures and the parallel plates are symmetrically positioned by a vertical plate. Then the bearing structure can be vertically pressed down or raised by a vertical spring at the lower end and two vertical folding members, thereby changing the distance with the parallel plates, and achieving the effect of changing the width of the test cavity. For this reason, it can effectively prevent the excessive loss of airflow of the jet structure to the edge caused by the excessive space of the test cavity. At the same time, the original multiple groups of locking structures can be replaced to position the blades according to the rebound effect, thereby improving the stability of the blade positioning test and the accuracy of the vibration test.

[0019] 2. The present invention is further improved by the anti-deflection device at the lower end of the vertical spring and the vertical folding part. The connection blocks 1 and 2 on the load-bearing plate can ensure the fixity of the lower end of the vertical spring and the vertical folding part to prevent tilting. Then, the three plug-in blocks at the lower end of the load-bearing plate and the linear insertion of the horizontal disassembly rod can ensure that the load-bearing plate is installed parallel and stably on the surface of the shock-absorbing base. Conversely, after the disassembly rod is pulled out, the plug-in block is released, so that the load-bearing plate can pull the entire bearing structure to the side through the connection blocks 1 and 2. The pulling control of the limit plate can improve the convenience of parallel removal of the test structure from the shock-absorbing base and the vertical plate area.

[0020] 3. After the restraining body is further improved, the overall verticality of the slide bar can be improved through the cross effect of the positioning block and the slide bar, and then the slide bar can increase its contact area with the center of the blade surface by using the side protrusion at the lower end. At the same time, the rubber protection block connected with the clamping block can directly contact the blade surface, so that the center surface of the blade will not be scratched when it is inserted and clamped in the center. Subsequently, when the slide bar slides, it can use the added reinforcement block and sliding layer to slide smoothly in the center of the positioning block, thereby preventing the occurrence of jamming. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 The present invention is a structural schematic diagram of an aero-engine blade vibration test device.

[0022] Figure 2 The present invention is a schematic diagram of a cross-sectional structure of an improved test structure.

[0023] Figure 3 The present invention is a schematic diagram of a cross-sectional structure of an improved load-bearing structure.

[0024] Figure 4 The present invention is a schematic diagram of the structure of an improved anti-deflection device when viewed from the front.

[0025] Figure 5 The present invention is a schematic cross-sectional structure diagram of a component arranged at the connection position between a disassembly rod and a vertical plate.

[0026] Figure 6 The present invention is a schematic diagram of the structure of a restraining body after improvement, viewed from the front.

[0027] Figure 7 The present invention is a schematic diagram of the cross-sectional structure of a component provided at the contact position between a sliding rod and the inner layer of a positioning block.

[0028] In the figure: shock-absorbing base-1, assembly layer-2, test structure-3, limit plate-4, electric control panel-5 Vertical plate-31, bearing structure-32, parallel plate-33, connecting block-34, jet structure-35, restraining body-36 Vibration detection module-321, solid block-322, power block-323, support block-324, vertical spring-325, vertical folding rod-326, anti-deflection device-327 Connecting block 1-3271, connecting block 2-3272, bearing plate-3273, insert block-3274, disassembly rod-3275 Slider-2751, Insert-2752, Adsorption block-2753, Plastic part-2754 Positioning block-361, slide bar-362, control block-363, side protrusion-364, card block-365, protection block-366 Auxiliary block-3621, reinforcing block-3622, sliding layer-3623, thread groove-3624, screw rod-3625. DETAILED DESCRIPTION

[0029] The present invention is further described below in conjunction with the accompanying drawings: Example

[0030] Figures 1 to 5 As shown: The present invention provides an aero-engine blade vibration test device. Its structure includes a shock-absorbing base 1, an assembly layer 2, a test structure 3, a limit plate 4, and an electric control panel 5. The upper end of the shock-absorbing base 1 positions the test structure 3 through the assembly layer 2, and the limit plate 4 is installed on the left and right sides of the test structure 3 and electrically controls the test structure 3 through the carried electric control panel 5.

[0031] The test structure 3 is provided with a bearing structure 32, one end of the bearing structure 32 is connected to the left and right sides of the middle and lower parts of the vertical plate 31 and the other end is connected to the inner layer of the limiting plate 4 through a connecting block 34. The upper part of the bearing structure 32 is communicated with the parallel plate 33 and the distance between the parallel plate 33 and the bearing structure 32 forms a detection cavity, and a restraining body 36 is arranged in the middle of the parallel plate 33, and the left and right sides thereof also include a jet structure 35, and the lower parts of the restraining body 36 and the jet structure 35 are communicated with the surface layer of the bearing structure 32.

[0032] Among them, the supporting structure 32 is provided with an anti-deflection device 327, and the center of the upper end of the anti-deflection device 327 is connected to a vertical spring 325 and vertical folding rods 326 on the left and right sides. The upper ends of the vertical folding rods 326 and the vertical springs 325 are inserted and embedded in the lower end of the support block 324. The upper layer of the support block 324 is also connected to a solid block 322, and the surface of the solid block 322 is fixed with a vibration detection module 321, which is embedded in the internal circuit of the vertical plate 31 through the power-on block 323 on the side to be electrically connected to the electric control panel 5.

[0033] Among them, two groups of bearing structures 32 and parallel plates 33 are symmetrically installed through the vertical plate 31 of the test structure 3, the bearing structure 32 overlaps with the surface of the shock-absorbing base 1 through the lower end anti-deflection device 327, and then the vertical spring 325 and the vertical folding rod 326 are used to control the height of the solid block 322 of the support block 324. When the height of the solid block 322 is adjusted, the distance from the parallel plate 33 is changed.

[0034] Among them, the shock-absorbing base 1 is arranged with a shock-absorbing wall in the vertical plate 31 of the test structure 3, and then carries a reinforcement plate and a shock-absorbing plug rod. The limit plates 4 on the left and right sides of the test structure 3 are both square in shape to determine the position of the electric control panel 5, and then the test structure 3 is electrically controlled through the power-carrying circuit.

[0035] Among them, the bearing structure 32 and the parallel plate 33 on the left and right sides of the vertical plate 31 are set in symmetrical positions and then connected with the limit plate 4 by means of a connecting block 34. The jet structure 35 carries a gas compressor inside, which can simulate high-speed airflow to test the blades. The restraining body 36 is arranged in the middle of the parallel plate 33.

[0036] Among them, the vibration detection module 321 is provided with one block on each of the left and right sides of the surface of the solid block 322 to contact the two sides of the blade, the power block 323 is a protrusion that can be inserted into the vertical plate 31 and electrically connected to the electric control panel 5, the vertical spring 325 is set at the middle distance between the two groups of vertical folding rods 326, and the bottom layer of the anti-deflection device 327 is a plane shape that overlaps with the surface of the shock-absorbing base 1.

[0037] Among them, the anti-deviation device 327 is provided with a disassembly rod 3275, and the disassembly rod 3275 passes through the side center of the plug block 3274 and is embedded in the lower end side part of the vertical plate 31 for fixed connection, so that the load-bearing plate 3273 on the plug block 3274 overlaps with the surface of the shock-absorbing base 1, and the upper end of the load-bearing plate 3273 is also provided with a connecting block 1 3271 and a connecting block 2 3272.

[0038] Among them, the connecting block 1 3271 and the connecting block 2 3272 are both in the shape of "concave" and one connecting block 3271 is provided on the left and right sides of the surface of the load-bearing plate 3273, three plug blocks 3274 are provided at the lower end of the load-bearing plate 3273, and a straight rail is opened in the center of the side of the plug block 3274 to allow the disassembly rod 3275 to pass through.

[0039] Among them, an adsorption block 2753 is also provided at one end of the disassembly and assembly rod 3275 connected to the side of the vertical plate 31, the right center of the adsorption block 2753 is connected to the left part of the insertion rod 2752 and a plastic part 2754 is also provided in the connection area, and the plastic part 2754 is arranged at the upper and lower ends of the adsorption block 2753, and the upper and lower ends of the insertion rod 2752 are also connected to the slider 2751 and the slider 2751 and the plastic part 2754 are matched with each other in spacing.

[0040] The slider 2751 is symmetrically positioned on the upper and lower surfaces of the insertion rod 2752 . The insertion rod 2752 and the adsorption block 2753 form a "T" shape, and two sets of plastic parts 2754 are small "L" shapes that cover the upper and lower edges of the adsorption block 2753 .

[0041] Specific functions and operation procedures of this embodiment: In the present invention, the aircraft engine blade vibration test device can determine the position of the test structure 3 through the assembly layer 2 of the shock-absorbing base 1, and then the test structure 3 can be installed in parallel through the limit plates 4 on the left and right sides, and then the jet structure 35 on the parallel plate 33 on the side of the vertical plate 31 of the electric control panel 5 and the vibration detection module 321 of the bearing structure 32 are electrically controlled, so that the vertical plate 31 will stand upright at the surface center of the shock-absorbing base 1, and then the two groups of bearing structures 32 and parallel plates 33 are symmetrically installed, and then the solid block 322 of the bearing structure 32 can be inserted into the vertical plate 31 through the power block 323 and electrically connected to the circuit, so that the vibration detection module 321 can be electrically connected to the electric control panel 5, and then the support block 324 at the lower end of the solid block 322 can be connected to the The vertical spring 325 and the upper end of the vertical folding rod 326 are connected. For this reason, the vertical spring 325 is pressed down after the blade is installed. During the process, the vertical folding member 326 can play a vertical auxiliary role to prevent tilting. Finally, the rebound effect of the vertical spring 325 can change the distance with the parallel plate 33, and then clamp the blade together with the parallel plate 33. Then, the containment body 36 on the parallel plate 33 is pressed down to overlap with the center of the blade to ensure the overlapping accuracy of the center. Then, the jet structure 35 simulates high-speed airflow to impact the blade through the internal gas compressor. At the same time, the generated vibration data can be fed back to the electric control panel 5 through the vibration detection module 321 to complete the vibration test. During the process, the containment body 36 and the rebound effect can be used to avoid the test cavity being too large. The large-scale loss of airflow and the replacement of the original multiple sets of locking components for locking one by one can effectively improve the stability and accuracy of the vibration test of the blades. Then, the anti-deflection device 327 at the lower end of the vertical spring 325 and the vertical folding rod 326 can be spliced ​​with the lower end of the vertical spring 325 and the vertical folding rod 326 through the connecting block 1 3271 and the connecting block 2 3272 on the load-bearing plate 3273, ensuring that they can be used in a stable vertical orientation. At the same time, the three plug blocks 3274 at the lower end of the load-bearing plate 3273 can be inserted into the shock-absorbing base 1 and then inserted through the straight disassembly rod 3275, so that the plug blocks 3274 and the shock-absorbing base 1 form a mutual restraint and reinforcement effect, and then the contact part of the disassembly rod 3275 and the vertical plate 31 can be connected through the adsorption block 27 53 is adsorbed and reinforced to prevent loosening. The adsorption block 2753 can be embedded in one end of the disassembly rod 3275 through the slider 2751 of the plug rod 2752, and the upper and lower edges of the adsorption block 2753 can be covered with two sets of plastic parts 2754 to prevent the adsorption block 2753 from being difficult to slide when it contacts and adsorbs the inside of the plug block 3274 when the disassembly rod 3275 is displaced. On the contrary, after the disassembly rod 3275 is removed from the plug block 3274 and the vertical plate 31 area, the restraining force of the plug block 3274 is released, so that the side of the bearing structure 32 is connected to the foundation with the limit plate 4 through the connecting block 34, and the limit plate 4 can be pulled in parallel to remove the test structure 3 as a whole from the assembly layer 2 of the shock-absorbing base 1, thereby forming a feature that is easy to disassemble and maintain. Example

[0042] Figure 6 to Figure 7 As shown: The present invention provides an aero-engine blade vibration test device. Its structure includes that the slider 2751 is set in a symmetrical position on the upper and lower surfaces of the insertion rod 2752, the insertion rod 2752 and the adsorption block 2753 form a "T" shape, and two groups of plastic parts 2754 are small "L" shapes to cover the upper and lower edges of the adsorption block 2753.

[0043] Among them, the positioning block 361 is connected to the middle part of the parallel plate 33 and intersects with the sliding rod 362. The side protrusion 364 at the lower end of the sliding rod 362 is wider than the lower end width of the sliding rod 362 and is restrained by the lower layer of the positioning block 361. The protection block 366 is a rubber product and is completely covered by the lower part of the sliding rod 362 and the side protrusion 364 through the embedding of the card block 365.

[0044] Among them, an auxiliary block 3621 is also provided in the internal contact area between the sliding rod 362 and the positioning block 361. The upper end of the auxiliary block 3621 is connected to the lower end of the reinforcing block 3622 and a sliding layer 3623 is provided on the upper layer of the reinforcing block 3622. A threaded groove 3624 is opened in the middle part of the sliding layer 3623, and the screw rod 3625 is locked through the threaded groove 3624.

[0045] The auxiliary block 3621 and the reinforcing block 3622 are perpendicular to each other and a linear threaded rail is opened in the center of the threaded groove 3624 to match with the screw rod 3625 .

[0046] Specific functions and operation procedures of this embodiment: In the present invention, the positioning block 361 of the restraining body 36 can be installed in parallel to the center of the parallel plate 33, and then the sliding rods 362 that cross each other in the middle can penetrate the middle of the parallel plate 33. Then, when the sliding rod 362 slides up and down through the control block 363, it can drive the reinforcing block 3622 added in the middle of the surface layer to slide. During the process, the finely polished sliding layer 3623 can prevent jamming during sliding. Then, when the reinforcing block 3622 is connected with the surface of the sliding rod 362, the auxiliary block 3621 is first inserted, and then the screw 3625 is locked by the thread groove 3624, so that the reinforcing block 3622 can be firmly connected with the sliding rod 362, thereby achieving the effect of easy disassembly and assembly. At the same time, the concave state of the thread groove 3624 can prevent the screw 362 from being stuck. The excessive protrusion of the top destroys the parallelism of the sliding layer 3623, but does not affect the normal upward and downward interaction stability of the sliding rod 362. The side protrusion 364 added to the lower end of the sliding rod 362 can be installed and covered by the protective block 366 through the clamping block 365. When the side protrusion 364 and the lower end of the sliding rod 362 are covered by the rubber protective block 366, they can directly contact the center of the surface of the blade, thereby increasing the friction between the two. Then, the load-bearing structure 32 and the parallel plate 33 are combined to increase the restraining force on the center of the blade, ensuring the stability of the blade during the vibration test without falling off. Subsequently, the cooperation of the rubber protective block 366 can avoid the mutual scraping of the surface caused by the direct contact between the metal surface and the blade, so that the effect of protecting the center of the surface of the blade can be achieved.

[0047] Utilizing the technical solution of the present invention, or those skilled in the art designing similar technical solutions inspired by the technical solution of the present invention to achieve the above-mentioned technical effects, all fall within the protection scope of the present invention.

Claims

1. An aero-engine blade vibration test device, the structure of which comprises: A shock-absorbing base (1), an assembly layer (2), a test structure (3), a limit plate (4), and an electric control panel (5), wherein the upper end of the shock-absorbing base (1) positions the test structure (3) through the assembly layer (2), and the limit plate (4) is installed on the left and right sides of the test structure (3) and electrically controls the test structure (3) through the carried electric control panel (5), characterized in that: The test structure (3) is provided with a bearing structure (32), one end of the bearing structure (32) is connected to the left and right sides of the middle and lower parts of the vertical plate (31), and the other end is connected to the inner layer of the limit plate (4) through a connecting block (34); the upper part of the bearing structure (32) is connected to the parallel plate (33), and the distance between the parallel plate (33) and the bearing structure (32) forms a detection cavity, and a restraining body (36) is provided in the middle of the parallel plate (33), and the left and right sides thereof also include an air jet structure (35); the lower parts of the restraining body (36) and the air jet structure (35) are both connected to the surface layer of the bearing structure (32); The bearing structure (32) is provided with an anti-deflection device (327), the center of the upper end of the anti-deflection device (327) is connected to a vertical spring (325) and the left and right sides include vertical folding rods (326), the upper ends of the vertical folding rods (326) and the vertical springs (325) are inserted and embedded in the lower end of the support block (324), the upper layer of the support block (324) is also connected to a solid block (322), and the surface of the solid block (322) is fixed with a vibration detection module (321), which is embedded in the internal circuit of the vertical plate (31) through the power supply block (323) on the side to be electrically connected to the electric control panel (5); The two groups of bearing structures (32) and parallel plates (33) are symmetrically installed through the vertical plate (31) of the test structure (3), the bearing structure (32) overlaps with the surface of the shock-absorbing base (1) through the lower end anti-deflection device (327), and then the height of the solid block (322) of the support block (324) is controlled by the vertical spring (325) and the vertical folding rod (326), and the distance between the solid block (322) and the parallel plate (33) is changed when the height of the solid block (322) is adjusted.

2. The aero-engine blade vibration test device according to claim 1, characterized in that: The shock-absorbing base (1) is provided with a shock-absorbing wall in the vertical plate (31) of the test structure (3), and furthermore, the base itself carries a reinforcement plate and a shock-absorbing plug rod. The limit plates (4) on the left and right sides of the test structure (3) are both square in shape to determine the position of the electric control panel (5), and then the test structure (3) is electrically controlled through the carried power lines.

3. The aero-engine blade vibration test device according to claim 1, characterized in that: The bearing structures (32) and the parallel plates (33) on the left and right sides of the vertical plate (31) are arranged in mutually symmetrical positions and then are interlaced and fixedly connected with the limit plates (4) by means of connecting blocks (34). The jet structure (35) carries a gas compressor inside to simulate high-speed airflow for testing the blades. The restraining body 36 is arranged in the middle of the parallel plates (33).

4. The aero-engine blade vibration test device according to claim 1, characterized in that: The vibration detection module (321) is provided with one block on each of the left and right sides of the surface of the solid block (322) to contact the two sides of the blades. The power supply block (323) is in a convex shape and can be inserted into the vertical plate (31) to be electrically connected to the electric control panel (5). The vertical spring (325) is arranged at the middle distance between the two groups of vertical folding rods (326). The bottom layer of the anti-deflection device (327) is in a flat shape and overlaps with the surface layer of the shock-absorbing base (1).

5. The aero-engine blade vibration test device according to claim 1, characterized in that: The deflection prevention device (327) is provided with a disassembly rod (3275), and the disassembly rod (3275) passes through the center of the side of the plug block (3274) and is embedded in the lower side of the vertical plate (31) for fixed connection, so that the load-bearing plate (3273) on the plug block (3274) overlaps the surface of the shock-absorbing base (1), and the upper end of the load-bearing plate (3273) is also provided with a connecting block 1 (3271) and a connecting block 2 (3272); The connecting block 1 (3271) and the connecting block 2 (3272) are both in the shape of a Chinese character "concave", and the connecting block 1 (3271) is provided with one block on each of the left and right sides of the surface of the load-bearing plate (3273). Three plug blocks (3274) are provided at the lower end of the load-bearing plate (3273), and a linear rail is opened at the center of the side of the plug block (3274) to allow the disassembly rod (3275) to pass through.

6. The aero-engine blade vibration test device according to claim 5, characterized in that: An adsorption block (2753) is also provided at one end of the disassembly and assembly rod (3275) connected to the side of the vertical plate (31); the center of the right side of the adsorption block (2753) is connected to the left side of the insertion rod (2752); and a plastic part (2754) is also provided in the connection area; the plastic part (2754) is arranged at the upper and lower ends of the adsorption block (2753); the upper and lower ends of the insertion rod (2752) are also connected to a slider (2751); and the slider (2751) and the plastic part (2754) are spaced in a coordinated manner; The slider (2751) is set in a symmetrical position on the upper and lower surfaces of the insertion rod (2752), the insertion rod (2752) and the adsorption block (2753) form a "T" shape, and the two groups of plastic parts (2754) are small "L" shapes to cover the upper and lower edges of the adsorption block (2753).

7. The aero-engine blade vibration test device according to claim 1, characterized in that: The restraining body (36) is provided with a slide bar (362), the upper end of the slide bar (362) passes through the central part of the positioning block (361) and is connected to a control block (363) at the upper end, the lower end of the slide bar (362) is also connected to a side protrusion (364) and the middle part is spliced ​​with a protection block (366) through a clamping block (365), so that the protection block (366) covers the lower end of the slide bar (362) and the side protrusion (364); The positioning block (361) is connected to the middle part of the parallel plate (33) and intersects with the slide bar (362); the side protrusion (364) at the lower end of the slide bar (362) has a width greater than the width of the lower end of the slide bar (362) and is restrained by the lower layer of the positioning block (361); the protection block (366) is made of rubber and completely covers the lower part of the slide bar (362) and the side protrusion (364) through the embedding of the clamping block (365).

8. The aero-engine blade vibration test device according to claim 7, characterized in that: An auxiliary block (3621) is also provided in the contact area between the slide rod (362) and the positioning block (361), the upper end of the auxiliary block (3621) is connected to the lower end of the reinforcing block (3622), and a sliding layer (3623) is provided on the upper layer of the reinforcing block (3622), and a thread groove (3624) is opened in the middle of the sliding layer (3623), and the screw rod (3625) is locked through the thread groove (3624); The auxiliary block (3621) and the reinforcing block (3622) are perpendicular to each other and a linear threaded rail is opened in the center of the threaded groove (3624) to match the screw rod (3625).

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