Multi-model aero-engine blade test fixture

Abstract

The invention relates to the technical field of engine blade detection, and discloses a multi-model aero-engine blade test fixture, which comprises a placement part, the placement part comprises a base, and the upper surface of the base is fixedly connected with a side plate; a reciprocating plate is slidably connected to the base through a sliding groove formed in the upper surface of the base, a two-way threaded rod penetrating through the interior of the reciprocating plate is rotatably connected to the interior of the side plate, and a connecting frame is fixedly connected to the side, away from the side plate, of the reciprocating plate. The multi-model aero-engine blade test fixture can effectively solve the problems that in the prior art, aero-engine blades are various in model, tenon structures and sizes of the blades of different models are remarkably different, a conventional fixture is of a fixed size design and cannot be compatible with the blades of different tenon types and sizes, and when the engine blades of different models are tested, the tenon structures and the sizes of the blades of different models are different. The whole set of clamp needs to be replaced, the test period is prolonged due to frequent replacement of the clamp, and the test steps are tedious.

Description

Technical Field

[0001] This invention relates to the field of engine blade testing technology, and specifically to a test fixture for blades of multiple types of aero-engines. Background Technology

[0002] As a core load-bearing component of an aero-engine, the mechanical properties of the blade directly determine the engine's operational safety and service life. During the blade's research and development, production, and maintenance phases, a series of tests are required to verify its structural load-bearing capacity and fatigue resistance. The clamping stability and adaptability of the test fixtures used to fix the tenons directly affect the accuracy of the test data and the testing efficiency.

[0003] In the existing technology, there are many types of aero-engine blades, and the tenon structure and size of different types of blades are significantly different. Conventional fixtures are designed with fixed dimensions and cannot be compatible with blades of different tenon types and sizes. When testing different types of engine blades, the entire set of fixtures needs to be replaced. Frequent fixture replacements prolong the testing cycle and make the testing procedures cumbersome. Summary of the Invention

[0004] To address the aforementioned shortcomings of existing technologies, this invention provides a multi-model aero-engine blade testing fixture, which effectively solves the problems of existing technologies where aero-engine blades come in a wide variety of models, with significant differences in tenon structures and dimensions between different models. Conventional fixtures are designed with fixed dimensions and cannot accommodate blades with different tenon types and sizes. When testing different models of engine blades, the entire fixture needs to be replaced, which frequently changes the fixture, prolongs the testing cycle, and makes the testing procedures cumbersome.

[0005] To achieve the above objectives, the present invention provides the following technical solution: This invention provides a multi-model aero-engine blade testing fixture, comprising: The placement part includes a base, and a side plate is fixedly connected to the upper surface of the base; The positioning part has a base that is slidably connected to a reciprocating plate via a groove on its upper surface. A bidirectional threaded rod that penetrates the reciprocating plate is rotatably connected inside the side plate. A connecting frame is fixedly connected to the side of the reciprocating plate away from the side plate. The connecting frame is provided with left and right clamping parts for clamping the tenon via a sliding groove on its side. The left and right clamping components include connecting rods that fit against the inner wall surface of the transfer groove. The inner surface of the connecting frame is provided with an elastic element that connects to the outer surface of the connecting rod. A connecting frame is fixedly connected to the side of the connecting rod away from the elastic element. A rolling rod is rotatably connected to the outer circumferential surface of the connecting frame.

[0006] Furthermore, the sliding groove is provided with several, and the outer circumferential surface of the rolling rod is designed to be made of rubber material that fits into the outer surface of the tenon.

[0007] Furthermore, a placement seat is fixedly connected to the upper surface of the middle part of the base, and front and rear clamping members are provided inside the placement seat. There are two side plates, which are symmetrically distributed with the placement seat as the center.

[0008] Furthermore, the outer end of the connecting rod passes through the sliding groove and is fixedly connected to a movable rod, and a slot is provided on the side of the movable rod near the connecting frame.

[0009] Furthermore, the outer surface of the connecting frame is damped and slidably connected to a connecting rod, and a locking block that fits against the inner wall surface of the slot is fixedly connected to the side of the connecting rod near the moving rod.

[0010] Furthermore, the outer edge of the slot is chamfered, and the top of the connecting rod extends to the upper surface of the connecting frame and is fixedly connected to a pressing plate.

[0011] Furthermore, the front and rear clamping components include a linkage block that is slidably connected to the interior of the placement seat, a hinge rod that is rotatably connected to the bottom end of the linkage block, and a clamping rod that is rotatably connected to the end of the hinge rod away from the linkage block.

[0012] Furthermore, an elastic layer is provided on the side of the clamping rod near the linkage block, and a spring connected to the lower surface of the linkage block is provided inside the placement seat.

[0013] The technical solution provided by this invention has the following advantages compared with the prior art: This invention features left and right clamping components and front and rear clamping components, enabling multi-directional positioning of blades of different models. The left and right clamping components contain multiple independent connecting rods, connecting frames, rolling rods, and elastic elements. When clamping irregularly shaped tenons with different cross-sectional widths, each rolling rod independently drives the corresponding connecting rod to slide in the sliding groove and compress the elastic element according to the actual width of the contact position. The elastic element generates differentiated rebound forces, allowing the clamping force to precisely match the complex contour of the tenon, forming a gradient pressure distribution. This achieves adaptive wrapping clamping for tenons of various structures and sizes without the need to replace parts, greatly improving the versatility and efficiency of the fixture. In the front and rear clamping components, after the tenon of the blade to be tested is placed, its own weight generates vertical pressure on the upper surface of the linkage block, driving the linkage block to move downwards along the vertical slide groove of the placement seat and compress the spring. During the downward movement of the linkage block, the pin drives the hinge rods on both sides to rotate synchronously, thereby pulling the clamping rods horizontally towards the tenon. Because the elasticity of the spring can adapt to the dimensional differences of the tenon in the front-to-back direction, and the elastic layer attached to the inside of the clamping rod can conform to the front and rear end faces of the tenon through its own deformation, flexible clamping in the front-to-back direction can be achieved without manual adjustment of the clamping spacing or replacement of parts. Together with the elastic wrapping of the left and right clamping parts, it forms a stable clamping system, effectively preventing the blade from loosening during the test and ensuring the accuracy and reliability of the static strength, fatigue, and dynamic characteristic test results. For different types of blades, there is no need to change the clamping parts, enabling rapid clamping of multiple models. Attached Figure Description

[0014] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the accompanying drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are merely some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without any creative effort.

[0015] Figure 1 This is a three-dimensional structural diagram of an embodiment of the present invention; Figure 2 This is a cross-sectional structural diagram of the base according to an embodiment of the present invention; Figure 3 This is an embodiment of the present invention. Figure 2 A magnified structural diagram of part A in the middle; Figure 4 This is a schematic diagram of the reciprocating plate, bidirectional threaded rod, and connecting frame according to an embodiment of the present invention; Figure 5 This is a cross-sectional structural diagram of the connecting frame according to an embodiment of the present invention; Figure 6 This is a cross-sectional structural diagram of the front and rear clamping members and the placement seat according to an embodiment of the present invention; Figure 7This is a schematic diagram of the structure of the left and right clamping components according to an embodiment of the present invention; Figure 8 This is an embodiment of the present invention. Figure 7 A magnified structural diagram of section B in the middle.

[0016] The labels in the diagram represent: 1. Placement part; 11. Base; 12. Side plate; 2. Positioning part; 21. Reciprocating plate; 22. Bidirectional threaded rod; 23. Connecting frame; 231. Moving groove; 24. Left and right clamping parts; 241. Connecting rod; 242. Elastic element; 243. Connecting frame; 244. Rolling rod; 245. Moving rod; 2451. Slot; 246. Connecting rod; 247. Locking block; 248. Pressing plate; 25. Placement seat; 26. Front and rear clamping parts; 261. Linkage block; 262. Hinge rod; 263. Clamping rod; 264. Spring. Detailed Implementation

[0017] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of the present invention. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without creative effort are within the scope of protection of the present invention.

[0018] The present invention will be further described below with reference to embodiments. Example:

[0019] Please see Figures 1-8 This invention provides a technical solution: a multi-type aero-engine blade testing fixture, comprising: Placement part 1, the placement part 1 includes a base 11, and a side plate 12 is fixedly connected to the upper surface of the base 11; The positioning part 2 and the base 11 are slidably connected to the reciprocating plate 21 through the slide groove opened on its upper surface. The side plate 12 is rotatably connected to the bidirectional threaded rod 22 that passes through the interior of the reciprocating plate 21. The reciprocating plate 21 is fixedly connected to the side away from the side plate 12. The connecting frame 23 is provided with left and right clamping parts 24 for clamping the tenon through the sliding groove 231 opened on its side. The left and right clamping members 24 include a connecting rod 241 that fits against the inner wall surface of the transfer groove 231. The inner surface of the connecting frame 23 is provided with an elastic element 242 that connects to the outer surface of the connecting rod 241. A connecting frame 243 is fixedly connected to the side of the connecting rod 241 away from the elastic element 242. A rolling rod 244 is rotatably connected to the outer circumference of the connecting frame 243.

[0020] Several grooves are provided in the sliding groove 231, and the outer circumferential surface of the rolling rod 244 is designed to be made of rubber material that fits into the outer surface of the tenon.

[0021] A placement seat 25 is fixedly connected to the upper surface of the middle part of the base 11. The placement seat 25 is provided with front and rear clamping members 26. There are two side plates 12, which are symmetrically distributed with the placement seat 25 as the center.

[0022] The outer end of the connecting rod 241 passes through the sliding groove 231 and is fixedly connected to the moving rod 245. The moving rod 245 has a slot 2451 on the side near the connecting frame 23.

[0023] The outer surface of the connecting frame 23 is damped and slidably connected to a connecting rod 246, and a locking block 247 that fits against the inner wall surface of the slot 2451 is fixedly connected to the side of the connecting rod 246 near the moving rod 245.

[0024] The outer edge of the slot 2451 is chamfered, and the top of the connecting rod 246 extends to the upper surface of the connecting frame 23 and is fixedly connected to the pressing plate 248.

[0025] The front and rear clamping members 26 include a linkage block 261 that is slidably connected to the inside of the placement seat 25. The bottom end of the linkage block 261 is rotatably connected to a hinge rod 262, and the end of the hinge rod 262 away from the linkage block 261 is rotatably connected to a clamping rod 263.

[0026] An elastic layer is provided on the side of the clamping rod 263 near the linkage block 261, and a spring 264 connected to the lower surface of the linkage block 261 is provided inside the placement seat 25.

[0027] The testing of aero-engine blades requires high accuracy in simulating the boundary conditions of the fixture. The fixture must accurately replicate the tenon constraint state of the blade inside the engine (i.e., the root is fixed and the blade body is free) to ensure that the clamping force is evenly distributed on the tenon contact surface and to avoid premature damage to the tenon due to local stress concentration, which would affect the authenticity of the test results.

[0028] The placement part 1 serves as the supporting base for the entire fixture, including a horizontally arranged base 11 and two side plates 12 vertically fixed to the upper surface of the base 11. The two side plates 12 are symmetrically distributed with the placement seat 25 in the middle of the base 11 as the center. The inner side of the side plate 12 is provided with threaded holes that match the outer surface of the bidirectional threaded rod 22, providing an installation and support reference for the positioning part 2. In the positioning part 2, the reciprocating plate 21 is slidably connected to the base 11 through a T-shaped groove on the upper surface of the base 11. The inner wall of the groove is in contact with the bottom sliding surface of the reciprocating plate 21, ensuring that the reciprocating plate 21 can only move back and forth in the horizontal direction and has no vertical displacement.

[0029] A bidirectional threaded rod 22 passes through the side plate 12 and the reciprocating plate 21. Its two ends are rotatably connected to the inside of the side plate 12 via bearings. The rod body is provided with bidirectional threads that mesh with the threaded holes inside the reciprocating plate 21. Rotating the bidirectional threaded rod 22 can drive the two reciprocating plates 21 to move synchronously in opposite directions. The connecting frame 23 is an inverted U-shaped frame structure, vertically fixed to the side of the reciprocating plate 21 away from the side plate 12. Several rectangular sliding grooves 231 are symmetrically opened on both side walls of the connecting frame 23. The sliding grooves 231 are evenly distributed along the height direction of the connecting frame 23, providing adjustable stroke for the left and right clamping parts 24. In the left and right clamping parts 24, the connecting rod 241 is a rectangular rod with its outer wall clearance fit with the inner wall of the sliding groove 231, allowing it to slide horizontally along the sliding groove 231. The elastic element 242 is a curved compression spring, with one end fixed to the inner surface of the connecting frame 23 and the other end connected to the boss on the outer surface of the connecting rod 241. In the initial state, the elastic element 242 is in a naturally elongated state, and the inner end of the connecting rod 241 protrudes from the inner side of the connecting frame 23. The connecting frame 243 is a U-shaped frame, vertically fixed to the inner end of the connecting rod 241. Its two side walls are rotatably connected to the rolling rod 244 through pins. The outer circumference of the rolling rod 244 is covered with a layer of wear-resistant rubber, and the surface of the rubber layer has anti-slip textures, which can increase the coefficient of friction and prevent damage to the tenon when it is in contact with the outer surface of the blade tenon. The movable rod 245 is vertically fixed to the outer end of the connecting rod 241. A rectangular slot 2451 is provided on the side near the connecting frame 23. The outer edge of the slot 2451 is chamfered to facilitate the quick insertion of the locking block 247. The connecting rod 246 is connected to the connecting frame 23 via a through slot on its outer surface with damping sliding. Multiple locking blocks 247 are fixedly connected to its outer surface, with the number of locking blocks 247 corresponding one-to-one with the movable slot 231. When the locking blocks 247 are in contact with the inner wall of the slot 2451, the position of the connecting rod 241 relative to the connecting frame 23 is locked. A pressing plate 248 is fixed to the top of the connecting rod 246 for easy pressing and adjustment by the operator.

[0030] The placement seat 25 is fixed to the upper surface of the middle part of the base 11, and its interior has a placement cavity for placing the front and rear clamping members 26. The front and rear clamping members 26 are symmetrically arranged on both sides of the hollow cavity of the placement seat 25. The linkage block 261 is a rectangular block that is slidably connected to the vertical groove inside the placement seat 25. Its upper surface is a planar structure, providing bottom support for the blade tenon, and its lower surface is fixedly connected to the top of the spring 264. The bottom end of the spring 264 is fixed to the bottom of the placement seat 25. In the initial state, the spring 264 is in a naturally extended state, and the top of the linkage block 261 protrudes from the bottom surface of the groove of the placement seat 25. At this time, the upper surface of the linkage block 261 is the highest point within its stroke range. The hinge rod 262 is rotatably connected to the outer bottom end of the linkage block 261 and the inner end of the clamping rod 263 via pins; the clamping rod 263 is an L-shaped rod with an elastic layer pasted on the side near the blade tenon, which can buffer the clamping force and is suitable for different tenon end faces; the surface of the elastic layer is in contact with the planes of both ends of the tenon to achieve flexible clamping in the front and back directions.

[0031] Initial state: When the blades are not clamped, the elastic element 242 in the left and right clamping parts 24 is in a naturally extended state, and the connecting rod 241 is in the moving groove 231 on the side away from the side plate 12. The connecting rod 241 drives the connecting frame 243 and the rolling rod 244 to protrude from the inside of the connecting frame 23 (extending towards the central placement seat 25). The slot 2451 on the moving rod 245 is separated from the locking block 247 on the outer surface of the connecting rod 246. The locking block 247 is held at its initial height by the damping force of the connecting rod 246. In the front and rear clamping parts 26, the spring 264 is in a naturally extended state, the top of the linkage block 261 protrudes from the upper surface of the placement seat 25, the hinge rod 262 pushes the clamping rod 263 to be in an open state, and the distance between the two clamping rods 263 is at its maximum, which can meet the placement of large-sized tenons.

[0032] The bidirectional threaded rod 22 is in the initial position, and the two reciprocating plates 21 drive the connecting frame 23 to the outermost position (close to the side plate 12). The distance between the left and right clamping parts 24 is at its maximum, which facilitates the insertion of the aero-engine blade tenon.

[0033] The process of placing the tenon of an aero-engine blade: The operator places the tenon of the aircraft engine blade to be tested vertically onto the upper surface of the mounting base 25 with the tenon facing downwards until the bottom of the tenon is in contact with the upper surface of the protruding linkage block 261. After the blade tenon is placed above the mounting base 25, the bottom of the tenon applies a vertical downward pressure to the top of the linkage block 261, pushing the linkage block 261 to slide downwards along the vertical groove of the mounting base 25, and the spring 264 is compressed.

[0034] During the downward movement of the linkage block 261, the pin drives the two hinge rods 262 on both sides to move vertically downward near one end of the linkage block 261. Correspondingly, the other end of the hinge rod 262 pulls the clamping rod 263 to slide horizontally towards the tenon (towards the linkage block 261). During this process, the blade hangs naturally, maintaining its free state. The two linkage blocks 261 inside the placement seat 25 move synchronously towards each other, and the distance between them gradually decreases, moving closer to the middle tenon until the elastic layer on the clamping rod 263 gradually fits tightly against the outer surfaces of the front and rear ends of the tenon. At this point, the front and rear clamping members 26 have completed the fixation of the blade tenon in the front-rear direction, and the two clamping rods 263 apply a stable clamping force to the front and rear surfaces of the tenon. The flexible design of the elastic layer can accommodate the planar structure of the front and back surfaces of different tenons, avoiding damage to the tenons, while the spring 264 can ensure the stability of the clamping process.

[0035] The process of positioning and clamping in the left and right directions: The side plate 12 is equipped with a drive motor that drives the bidirectional threaded rod 22 to rotate. Since the bidirectional threaded rod 22 is engaged with the reciprocating plate 21 and the reciprocating plate 21 is constrained by the sliding groove of the base 11 and can only move horizontally, the two reciprocating plates 21 move synchronously towards each other, the distance between them gradually decreases, and drives the connecting frames 23 on both sides and the left and right clamping parts 24 to move closer to the middle tenon.

[0036] As the reciprocating plate 21 moves, the rubber layer on the outer surface of the rolling rod 244 gradually comes into close contact with the left and right surfaces of the tenon. The tenon applies a horizontal reaction force to the rolling rod 244, pushing the connecting rod 241 to slide outward along the sliding groove 231, compressing the elastic element 242. The elastic element 242 generates a reverse elastic force, which is transmitted to the rolling rod 244 through the connecting rod 241 and the connecting frame 243, causing the rolling rod 244 to tightly press against the left and right surfaces of the tenon, achieving elastic clamping in the left and right directions.

[0037] Because there are many types of aero-engine blades, the tenon structures (such as dovetail tenons, fir tenons, and rectangular tenons) and dimensions (tenon width, height, tooth angle, and tooth tip clearance) of different types of blades vary significantly. Therefore, the specific positions and contact angles of the multiple rolling rods 244 evenly arranged along the height direction of the connecting frame 23 with the left and right sides of the tenon will vary depending on the tenon structure. This results in a personalized distribution of the compressive force and compression amount of the elastic elements 242 corresponding to the connecting rods 241 at different heights. Ultimately, the differentiated rebound of the elastic elements 242 achieves precise fitting and reliable clamping of different tenon contours.

[0038] Taking a dovetail tenon as an example: the dovetail tenon has symmetrical bevels on both sides, and its width gradually increases from top to bottom. When the reciprocating plate 21 moves the left and right clamping parts 24 closer to the tenon, the rolling rods 244 at different heights will contact the dovetail tenon bevels in sequence: the upper rolling rod 244 first contacts the narrow end bevel of the tenon, and the horizontal reaction force it receives is small. The corresponding connecting rod 241 slides outward along the sliding groove 231 for a shorter distance, and the elastic element 242 has a smaller compression amount. As the reciprocating plate 21 continues to move, the middle and lower rolling rods 244 successively contact the middle and wide end bevels of the tenon. Since the width of the tenon increases from top to bottom, the horizontal reaction force received by the lower rolling rod 244 is greater than that of the upper one. The corresponding connecting rod 241 slides for a longer distance, and the elastic element 242 has a larger compression amount. At this time, the elastic elements 242 at each height generate differentiated rebound forces according to the tenon width at the contact position: the lower elastic element 242 has a stronger rebound force, while the upper elastic element 242 has a relatively weaker rebound force, forming a gradient clamping force that matches the inclination angle of the dovetail tenon. Under the action of the elastic force, the rolling rod 244 fits tightly against the inclination, and at the same time, the rolling rod 244 can rotate along its own axis to adaptively adjust the contact angle, avoiding local stress concentration caused by the inclination contact, and ensuring the full wrapping clamping of the dovetail tenon in the left and right directions.

[0039] The rolling rods 244 at different heights independently adjust their contact state according to the changes in the cross-sectional profile of each segment of the tenon: for areas where the cross-sectional width increases, the reaction force on the rolling rod 244 increases, the sliding distance of the connecting rod 241 extends, and the compression of the elastic element 242 increases; for areas where the cross-sectional width decreases, the compression of the elastic element 242 decreases, and the rebound force decreases accordingly. Through differentiated compression and rebound, the tenon automatically conforms to the complex profile of the variable cross-section tenon, achieving reliable fixation of the variable cross-section tenon without additional adjustment of the clamping structure. The rubber layers of multiple rolling rods 244 form a multi-point uniform clamping structure, ensuring that the clamping force is evenly distributed along the height direction of the tenon, avoiding tenon deformation due to uneven local force.

[0040] When the clamping force reaches the preset value, the rotation of the bidirectional threaded rod 22 stops. At this time, the operator presses down on the pressing plate 248, causing the connecting rod 246 to slide down the through groove on the outer surface of the connecting frame 23 with damping. The locking block 247, guided by the chamfer of the locking groove 2451, engages inside the locking groove 2451, fitting tightly against the inner wall of the locking groove 2451, thus locking the position of the connecting rod 241. At this point, the aero-engine blade tenon is completely and omnidirectionally clamped and fixed, preventing the connecting rod 241 from loosening due to vibration during testing.

[0041] State maintenance during testing After clamping, the blade tenon is positioned in multiple directions by the left and right clamping parts 24 and the front and rear clamping parts 26. The root of the tenon is completely fixed, and the blade body remains in a free hanging state, ensuring the constraint conditions during testing. When performing static strength tests, low-cycle fatigue tests, or dynamic characteristic tests, the load is transmitted to the tenon through the fixture base 11, the placement seat 25, and the clamping members. The locking structure of the locking blocks 247 and the slots 2451 of the left and right clamping members 24 prevents the connecting rod 241 from shifting. The springs 264 of the front and rear clamping members 26 ensure stable clamping force. The rubber layer of the rolling rod 244 and the elastic layer of the clamping rod 263 can buffer the load impact and prevent the tenon from slipping or being damaged.

[0042] The process of blade disassembly: After the test is completed, the operator pulls the pressing plate 248 upward, which moves the connecting rod 246 upward, causing the locking block 247 to disengage from the slot 2451 and releasing the locking of the connecting rod 241.

[0043] Rotating the bidirectional threaded rod 22 counterclockwise drives the two reciprocating plates 21 to move in opposite directions. The left and right clamping parts 24 move away from the tenon, and the elastic element 242 returns to its natural extension state. The connecting rod 241 drives the rolling rod 244 to reset. Lifting the blade upwards removes the pressure of the bottom of the tenon on the linkage block 261. The spring 264 returns to its natural extension state, pushing the linkage block 261 upwards. The hinge rod 262 drives the clamping rod 263 to open, and the tenon smoothly disengages from the clamp, completing the disassembly.

[0044] In summary, this aero-engine blade testing fixture has the following advantages: Advantage 1: Traditional clamps are designed with fixed dimensions, and one type of clamp is only suitable for a single type of blade, such as fir tenon or dovetail tenon. When facing tenons with different contours, it is necessary to change the clamp or make complicated adjustments, resulting in poor versatility. However, this invention achieves multi-directional positioning of different types of blades through left and right clamping parts 24 and front and rear clamping parts 26.

[0045] The left and right clamping components 24 are equipped with multiple independent connecting rods 241, connecting frames 243, rolling rods 244, and elastic elements 242. When clamping irregularly shaped tenons with different cross-sectional widths, each rolling rod 244 independently drives the corresponding connecting rod 241 to slide in the sliding groove 231 and compress the elastic element 242 according to the actual width of the contact position. The elastic element 242 generates differentiated rebound force, enabling the clamping force to accurately match the complex contour of the tenon, forming a gradient pressure distribution. This achieves adaptive wrapping clamping for tenons of various structures and sizes without the need to replace parts, greatly improving the versatility and efficiency of the clamp.

[0046] In the front and rear clamping components 26, after the tenon of the blade to be tested is placed, its own weight will generate vertical pressure on the upper surface of the linkage block 261, driving the linkage block 261 to move down along the vertical slide groove of the placement seat 25 and compress the spring 264. During the downward movement of the linkage block 261, the hinge rods 262 on both sides are driven to rotate synchronously through the pin, thereby pulling the clamping rod 263 to move horizontally towards the tenon. Since the elastic extension and contraction characteristics of the spring 264 can adapt to the size difference of the tenon in the front and rear directions, and the elastic layer pasted on the inner side of the clamping rod 263 can conform to the front and rear end faces of the tenon through its own deformation, flexible clamping in the front and rear directions can be achieved without manual adjustment of the clamping spacing or replacement of parts. Together with the elastic wrapping of the left and right clamping components 24, it constitutes a stable clamping system, effectively preventing the blade from loosening during the test and ensuring the accuracy and reliability of the static strength, fatigue and dynamic characteristic test results.

[0047] For different blade models, there is no need to change the clamping components, enabling rapid clamping of multiple models. Advantage 2: Traditional rigid clamps, when clamping, have a hard contact between the clamping surface and the blade tenon. This can easily scratch or crush the delicate tenon surface due to excessive clamping force or stress concentration at the contact point, causing irreversible damage. This invention employs a flexible design in all parts that directly contact the tenon: the left and right clamping rolling rods 244 are wrapped with a wear-resistant rubber layer with anti-slip texture, and the front and rear clamping rods 263 have an elastic layer adhered to their surfaces. These flexible layers not only increase the coefficient of friction to prevent slippage, but more importantly, they act as a buffer, absorbing impacts during clamping and vibration loads during testing, thus avoiding damage to the tenon surface. This is particularly suitable for high-value aero-engine blades.

[0048] Thirdly, existing clamps typically require additional tools such as wrenches and screwdrivers for locking after being positioned, which is cumbersome and time-consuming. In this invention, once the clamping force reaches a preset value, the operator only needs to press down on the pressing plate 248. The engagement of the locking block 247 and the locking slot 2451 instantly locks the positions of all movable connecting rods 241, making the operation simple and quick. For disassembly, lifting the pressing plate 248 unlocks the clamp, and the blades are quickly released by the reverse rotation of the bidirectional threaded rod 22 and the springs 264 in the front and rear clamping parts 26. The entire clamping and disassembly process requires no tools, simplifying the process and significantly improving the efficiency of test preparation and completion.

[0049] Fourthly, when testing the vibration characteristics of blades, the blade body must be in a completely unconstrained, free-hanging state to obtain its true dynamic parameters. Existing fixtures often have complex structures that may accidentally touch or constrain the blade body when clamping the tenon. This invention concentrates all clamping and positioning functions in the tenon area. The bottom of the tenon is supported by the linkage block 261 within the placement seat 25, and the left and right clamping members 24 and the front and rear clamping members 26 surround the tenon from all sides. The entire clamping process involves no contact with the blade body, ensuring that the blade body remains free from installation to testing. This allows for a more realistic simulation of the actual working state of blades in an engine, improving the effectiveness of the test and its engineering reference value.

[0050] The above embodiments are only used to illustrate the technical solutions of the present invention, and are not intended to limit it. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features. Such modifications or substitutions will not cause the essence of the corresponding technical solutions to deviate from the protection scope of the technical solutions of the embodiments of the present invention.

Claims

1. A test fixture for multi-type aero-engine blades, characterized in that, include: Placement part (1), the placement part (1) includes a base (11), and a side plate (12) is fixedly connected to the upper surface of the base (11). The positioning part (2) has a base (11) that is slidably connected to a reciprocating plate (21) through a groove on its upper surface. The side plate (12) is rotatably connected to a bidirectional threaded rod (22) that passes through the inside of the reciprocating plate (21). A connecting frame (23) is fixedly connected to the side of the reciprocating plate (21) away from the side plate (12). The connecting frame (23) is provided with left and right clamping parts (24) for clamping the tenon through a sliding groove (231) on its side. The left and right clamping members (24) include a connecting rod (241) that fits against the inner wall surface of the transfer groove (231). The inner surface of the connecting frame (23) is provided with an elastic element (242) that connects to the outer surface of the connecting rod (241). A connecting frame (243) is fixedly connected to the side of the connecting rod (241) away from the elastic element (242). A rolling rod (244) is rotatably connected to the outer circumferential surface of the connecting frame (243).

2. The multi-model aero-engine blade testing fixture according to claim 1, characterized in that: The shift groove (231) has several openings, and the outer circumferential surface of the rolling rod (244) is designed with a rubber material that fits in conjunction with the outer surface of the tenon.

3. The multi-model aero-engine blade testing fixture according to claim 1, characterized in that: The upper surface of the middle part of the base (11) is fixedly connected to a placement seat (25). The placement seat (25) is provided with front and rear clamping parts (26). There are two side plates (12), which are symmetrically distributed with the placement seat (25) as the center.

4. The multi-model aero-engine blade testing fixture according to claim 1, characterized in that: The outer end of the connecting rod (241) passes through the sliding groove (231) and is fixedly connected to the moving rod (245). The moving rod (245) has a slot (2451) on the side near the connecting frame (23).

5. A multi-model aero-engine blade testing fixture according to claim 4, characterized in that: The outer surface of the connecting frame (23) is damped and slidably connected to a connecting rod (246), and a card block (247) that fits against the inner wall surface of the card slot (2451) is fixedly connected to the side of the connecting rod (246) near the moving rod (245).

6. A multi-model aero-engine blade testing fixture according to claim 5, characterized in that: The outer edge of the slot (2451) is chamfered, and the top of the connecting rod (246) extends to the upper surface of the connecting frame (23) and is fixedly connected to the pressing plate (248).

7. A multi-model aero-engine blade testing fixture according to claim 3, characterized in that: The front and rear clamping members (26) include a linkage block (261) that is slidably connected to the inside of the placement seat (25). The bottom end of the linkage block (261) is rotatably connected to a hinge rod (262), and the end of the hinge rod (262) away from the linkage block (261) is rotatably connected to a clamping rod (263).

8. A multi-model aero-engine blade testing fixture according to claim 7, characterized in that: The clamping rod (263) has an elastic layer on the side near the linkage block (261), and the placement seat (25) has a spring (264) connected to the lower surface of the linkage block (261).

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