Fatigue test fixture for aircraft blade

Abstract

The utility model discloses an aircraft blade fatigue test fixture which comprises a clamping mechanism used for clamping an engine blade, the clamping mechanism is arranged at the top of a base mechanism, and the base mechanism is arranged at the top of a base; through the arrangement of a positioning base, a sliding base, limiting blocks, a clamp positioning frame and other parts in the base mechanism, the clamp positioning frame can rotate by 90 degrees and be clamped with any set of limiting blocks through the cooperation relation of a cross-shaped clamping groove formed by the limiting blocks and a second base, the clamp positioning frame and a positioning column, and therefore the clamp positioning frame can be clamped with any set of limiting blocks; and the clamping direction of the clamping mechanism is adjusted. Therefore, the device can perform fatigue testing on the aircraft engine blade in different directions through the angle adjusting function of the base mechanism, and the universality and the testing flexibility of the clamp are improved.

Description

Technical Field

[0001] This utility model relates to the field of aerospace manufacturing technology, specifically: a fatigue testing fixture for aircraft blades. Background Technology

[0002] As a core component of aero engines, aircraft engine blades operate continuously under extreme conditions of high temperature, high pressure, and high speed, making them highly susceptible to fatigue damage. Fatigue testing is a crucial step in evaluating blade performance and ensuring flight safety, and its results directly affect the reliability and service life of aircraft engines.

[0003] Currently, traditional aircraft blade fatigue testing fixtures suffer from numerous problems in practical applications. Some fixtures have a simplistic structure, making it difficult to flexibly adjust the blade clamping angle and direction, and thus failing to simulate the complex stress states of blades within the engine, leading to significant deviations between test results and actual operating conditions. Furthermore, existing clamping methods are inadequate in securing the blades, making them prone to loosening or even detachment during prolonged, high-frequency fatigue testing. This not only affects the accuracy of test data but also poses safety hazards. In addition, traditional fixtures are cumbersome to replace and maintain components, increasing testing costs and time, and reducing testing efficiency.

[0004] No effective solutions have yet been proposed to address the problems in the relevant technologies. Utility Model Content

[0005] In view of the problems in the related technologies, this utility model proposes an aircraft blade fatigue testing fixture to overcome the above-mentioned technical problems existing in the existing related technologies.

[0006] Therefore, the specific technical solution adopted by this utility model is as follows:

[0007] An aircraft blade fatigue testing fixture includes a clamping mechanism for clamping engine blades, the clamping mechanism being disposed on top of a base mechanism, the base mechanism being disposed on top of a base.

[0008] The base mechanism includes a positioning base fixed at the top of the base and a sliding base that can adjust the clamping direction of the clamping mechanism. The sliding base includes a second base movably mounted on the top of the base, a positioning post for limiting the clamping positioning frame, a clamping positioning frame for supporting the clamping mechanism, and a limiting block for stabilizing the clamping positioning frame. The limiting block includes four sets, and the limiting block cooperates with the second base to form a cross-shaped groove. The clamping positioning frame can rotate 90° to adjust the installation direction of the clamping mechanism.

[0009] Optionally, the clamping mechanism includes a first transverse clamp disposed on the top of the positioning base, a second transverse clamp disposed on the top of the sliding base, and a spare longitudinal clamp. The first transverse clamp, the second transverse clamp, and the longitudinal clamp each include a second side plate for fixing and installing the slide, a slide for movably installing the clamping plate, and a bidirectional bolt rod for driving the clamping plate to clamp the blade. A secondary pressing rod is threaded onto one side of the clamping plate. The bidirectional bolt rod drives the clamping plate to move in opposite directions or backwards, realizing the rapid clamping and releasing of the blade. The secondary pressing rod includes a screw, a spherical pressing block, and an internal hexagonal nut. The secondary pressing rod screw + spherical pressing block are adapted to the wavy groove at the root of the blade to enhance clamping stability. The spherical pressing block is used to clamp the wavy groove at the root of the blade. An internally threaded slider is fixedly connected to one side of the clamping plate. The internally threaded slider is movably installed on one side of the slide.

[0010] Optionally, the positioning base includes a first base fixedly installed on the top of the base and a first side plate fixedly connected to the left and right sides of the first base, wherein the first side plate is used to fix the first transverse clamp.

[0011] Optionally, the top of the second base is provided with a locking hole for inserting the locking block at the bottom of the limiting block. The top of the fixture positioning frame is provided with a limiting hole for fixing the fixture positioning frame with the positioning column. The positioning column restricts the movement of the fixture positioning frame to ensure the accuracy of the test position. A pad is fixedly connected to one side of the fixture positioning frame for connecting the output end of the fatigue testing machine.

[0012] Optionally, each side of the clamp positioning frame is provided with a clamp mounting hole for fixing the second side plate with bolts.

[0013] Optionally, the slides inside the first and second transverse clamps are arranged transversely, and the slides inside the longitudinal clamp are arranged longitudinally.

[0014] Optionally, the fixture positioning frame can be rotated to engage with any set of limiting blocks in the cross-shaped slot to achieve 90° interval angular positioning.

[0015] The beneficial effects of this utility model are as follows: By setting up components such as a positioning base, sliding base, limiting block, and fixture positioning frame in the base mechanism, and through the cross-shaped groove formed by the limiting block and the second base, and the cooperation relationship between the fixture positioning frame and the positioning post, the fixture positioning frame can be rotated 90° and engaged with any set of limiting blocks, thereby adjusting the clamping direction of the clamping mechanism. This achieves the effect of enabling the device to perform fatigue testing on aircraft engine blades in different directions through the angle adjustment function of the base mechanism, improving the versatility and testing flexibility of the fixture. By setting up components such as a first transverse clamp, a second transverse clamp, a longitudinal clamp, a bidirectional bolt rod, and a secondary pressing rod in the clamping mechanism, and through the bidirectional bolt rod driving the clamping plate to move, and the cooperation relationship between the spherical pressing block of the secondary pressing rod and the wavy groove at the blade root, the clamping plate can stably clamp the engine blade through the drive of the bidirectional bolt rod and the auxiliary pressing of the secondary pressing rod. This allows the device to reliably fix different types of blades and meet the clamping accuracy requirements for fatigue testing through multi-directional clamping of the clamping mechanism and adaptive top pressure structure, thus avoiding stress concentration problems during blade clamping. Attached Figure Description

[0016] To more clearly illustrate the technical solutions in the embodiments of this utility model or the prior art, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0017] Figure 1 This is a schematic diagram of the overall structure of the aircraft blade fatigue testing fixture according to an embodiment of the present utility model;

[0018] Figure 2 This is a partial structural schematic diagram of the aircraft blade fatigue testing fixture according to an embodiment of the present utility model;

[0019] Figure 3 This is a partial structural diagram of the clamping mechanism according to an embodiment of the present utility model;

[0020] Figure 4 This is a partial structural diagram of the base mechanism according to an embodiment of the present utility model;

[0021] Figure 5 This is a partial structural installation diagram of the base mechanism according to an embodiment of the present utility model;

[0022] Figure 6 This is a partial structural installation diagram of the clamping mechanism according to an embodiment of the present utility model;

[0023] Figure 7This is a detailed schematic diagram of the clamping mechanism parts according to an embodiment of the present utility model.

[0024] In the picture:

[0025] 1. Base; 2. Base mechanism; 21. Positioning base; 22. Sliding base; 201. First base; 202. First side plate; 203. Second base; 204. Locking hole; 205. Positioning post; 206. Limiting block; 207. Fixture positioning frame; 208. Limiting hole; 209. Pad; 3. Clamping mechanism; 31. First transverse clamp; 32. Second transverse clamp; 33. Longitudinal clamp; 301. Second side plate; 302. Slide seat; 303. Two-way bolt rod; 304. Clamping plate; 305. Secondary top pressure rod; 306. Internal threaded slider. Detailed Implementation

[0026] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0027] According to an embodiment of the present invention, an aircraft blade fatigue testing fixture is provided.

[0028] Please see Figure 1 An aircraft blade fatigue testing fixture includes a clamping mechanism 3 for holding engine blades. The clamping mechanism 3 is disposed on top of a base mechanism 2, which is disposed on top of a base 1. This structural design ensures stable clamping of the blades during testing, providing a reliable foundation for accurate testing and enabling the entire testing process to be carried out in an orderly manner.

[0029] Please see Figures 2 to 7 The base mechanism 2 includes a positioning base 21 fixed at the top of the base 1 and a sliding base 22 that adjusts the clamping direction of the clamping mechanism 3. The sliding base 22 includes a second base 203 movably mounted on the top of the base 1, a positioning post 205 for limiting the clamping positioning frame 207, a clamping positioning frame 207 for supporting the clamping mechanism 3, and limiting blocks 206 for stabilizing the clamping positioning frame 207. The limiting blocks 206 comprise four sets, which, together with the second base 203, form a cross-shaped slot. The clamping positioning frame 207 can rotate 90° to adjust the installation direction of the clamping mechanism 3. This flexible design allows for adjustment of the blade clamping angle according to different testing requirements, significantly improving the applicability and versatility of the testing.

[0030] The clamping mechanism 3 includes a first transverse clamp 31 mounted on the top of the positioning base 21, a second transverse clamp 32 mounted on the top of the sliding base 22, and a spare longitudinal clamp 33. Each of the first transverse clamp 31, the second transverse clamp 32, and the longitudinal clamp 33 includes a second side plate 301 for fixing the slide 302, a slide 302 for movably mounting the clamping plate 304, and a bidirectional bolt rod 303 for driving the clamping plate 304 to clamp the blade. A secondary pressing rod 305 is threaded onto one side of the clamping plate 304. The secondary pressing rod 305 includes a screw, a spherical pressing block, and an internal hexagonal nut. The spherical pressing block is used to clamp the wavy groove at the root of the blade. An internally threaded slider 306 is fixedly connected to one side of the clamping plate 304 and is movably mounted on one side of the slide 302. The diverse clamping methods and secondary pressing design ensure a stable clamping of the blade from all directions, preventing the blade from loosening during testing and affecting the test results.

[0031] The positioning base 21 includes a first base 201 fixedly installed on the top of the base 1 and first side plates 202 fixedly connected to the left and right sides of the first base 201. The first side plates 202 are used to fix the first transverse clamp 31. The positioning base 21 provides stable support for the first transverse clamp 31, ensuring that it maintains a fixed posture during testing and enhancing the stability and reliability of the test.

[0032] The top of the second base 203 is provided with a locking hole 204 for inserting the locking block at the bottom of the limiting block 206. The top of the fixture positioning frame 207 is provided with a limiting hole 208 for fixing the fixture positioning frame 207 in place with the positioning column 205. A pad 209 is fixedly connected to one side of the fixture positioning frame 207 for connecting the output end of the fatigue testing machine. The cooperation of the locking hole 204 and the limiting hole 208 enables precise positioning and fixing of the fixture positioning frame 207, while the pad 209 effectively transmits the force of the testing machine, ensuring the smooth progress of the test.

[0033] Each side of the clamp positioning frame 207 is provided with a clamp mounting hole 310 for fixing the second side plate 301 with bolts. The clamp mounting hole facilitates the installation and disassembly of the clamping mechanism 3, makes it easier to maintain and replace parts later, and improves the ease of use of the clamp.

[0034] The slides 302 inside the first transverse clamp 31 and the second transverse clamp 32 are arranged transversely, while the slides 302 inside the longitudinal clamp 33 are arranged longitudinally. The arrangement of the slides 302 in different directions allows the three clamps to hold the blades from multiple dimensions, meeting the needs of diverse testing scenarios and enriching the testing methods.

[0035] The fixture positioning frame 207 rotates to engage with any set of limit blocks 206 in the cross-shaped slot, achieving 90° angular positioning. This angular positioning method is simple and efficient, allowing for quick adjustment of the clamping mechanism in three directions, saving time for testers and improving testing efficiency.

[0036] In practical applications, when conducting lateral fatigue tests on the compressor blades of a certain type of passenger aircraft engine, the testers first place the base 1 on a stable test platform, and then begin installing the base mechanism 2. The first base 201 of the positioning base 21 is bolted to the top of the base 1. The first side plates 202 on both sides of the first base 201 are horizontal at this time, for subsequent fixing and installation of the first lateral clamp 31. Next, the sliding base 22 is installed, and the second base 203 is movably installed on the top of the base 1. The locking blocks at the bottom of the four sets of limiting blocks 206 are inserted into the locking holes 204 at the top of the second base 203, thus forming a cross-shaped locking groove with the four sets of limiting blocks 206 and the second base 203. Then, the clamp positioning frame 207 is placed in the cross-shaped locking groove. At this time, the positioning pin 205 is inserted into the limiting hole 208 at the top of the clamp positioning frame 207 to limit the position of the clamp positioning frame 207, while the limiting blocks 206 stabilize the clamp positioning frame 207. Next, the clamping mechanism 3 is installed. The second side plate 301 of the first transverse clamp 31 is fixedly installed on the first side plate 202 at the top of the positioning base 21 using bolts. The slide 302 inside the first transverse clamp 31 is then positioned transversely. On one side of the clamp positioning frame 207 at the top of the sliding base 22, the second side plate 301 of the second transverse clamp 32 is fixedly installed using the clamp mounting holes 310 and bolts. The slide 302 inside the second transverse clamp 32 is also positioned transversely.

[0037] The compressor blade to be tested is placed between the first transverse clamp 31 and the second transverse clamp 32. The double-acting bolt 303 is turned, driving the clamping plate 304 to slide on the slide block 302, gradually bringing the clamping plate 304 closer to the blade. Once the clamping plate 304 contacts the blade, the double-acting bolt 303 is turned until the clamping plate 304 firmly clamps the blade. Then, a secondary pressure rod 305 is threaded onto one side of the clamping plate 304, ensuring that the spherical pressure block of the secondary pressure rod 305 accurately abuts against the wavy groove at the root of the blade, further ensuring the blade is securely clamped and preventing loosening during testing.

[0038] A pad 209 fixedly connected to one side of the fixture positioning frame 207 is connected to the output end of the fatigue testing machine to ensure stable power transmission. During the test, if it is necessary to adjust the installation direction of the clamping mechanism 3 to simulate different stress conditions, the tester can rotate the fixture positioning frame 207 90° in the cross-shaped slot. At this time, the fixture positioning frame 207 cooperates with another set of limit blocks 206 to achieve angular positioning at 90° intervals. The positioning post 205 still restricts the position of the fixture positioning frame 207 to ensure stability after rotation, thereby continuing to carry out fatigue tests in different directions.

[0039] The implementation principle of an aircraft blade fatigue testing fixture according to an embodiment of this application is as follows:

[0040] First, place the base 1 stably on the test platform and use bolts or other fixing methods to ensure its stability. Fix the positioning base 21 on the top of the base 1 to provide stable support for the first transverse clamp 31. At the same time, movably install the second base 203 on the base 1 as the basis for the sliding base 22. Insert the limiting block 206 into the card hole 204 on the top of the second base 203 to form a cross-shaped card slot, which prepares for the subsequent installation and orientation adjustment of the clamp positioning frame 207.

[0041] Secondly, depending on the specific directional requirements of the aircraft engine blade fatigue test, either laterally or longitudinally, rotate the fixture positioning frame 207. The fixture positioning frame 207 can rotate 90° around the positioning post 205. When rotated to the target angle, the limiting hole 208 at the top is precisely aligned with the positioning post 205. Insert the fixing pin or bolt to fix the fixture positioning frame 207 in the corresponding limiting block 206 position in the cross-shaped slot, realize the 90° interval angle positioning, and complete the adjustment of the test direction of the clamping mechanism 3.

[0042] Next, based on the determined test direction, select a suitable fixture for installation. If it is a lateral test, install the first lateral fixture 31 on the positioning base 21, or install the second lateral fixture 32 on the sliding base 22 whose direction has been adjusted. If it is a longitudinal test, install the longitudinal fixture 33, place the aircraft engine blade between the clamping plates 304, and drive the clamping plates 304 to move along the slide 302 by rotating the double-acting bolt rod 303 to initially clamp the blade. Subsequently, turn the secondary pressure rod 305 to make the spherical pressure block fit tightly against the wavy groove at the root of the blade, further stabilizing the blade and ensuring that the blade will not shift during the test.

[0043] Next, connect the pad 209 on one side of the fixture positioning frame 207 to the output end of the fatigue testing machine to ensure that the connection is firm and reliable and can stably transmit various loads output by the testing machine. At the same time, check whether the connections between the various components of the equipment are tight and whether the wiring is correctly connected, and confirm that the entire testing system is in normal working condition, so as to prepare for the formal start of the test.

[0044] Finally, after confirming that all installation and connection work is correct, the fatigue testing machine is started, and periodic loads are applied to the blade according to the preset test parameters. During the test, the stress, strain, displacement and other data of the blade are collected in real time by the sensors installed on the equipment and transmitted to the data acquisition system for analysis and recording. When the blade develops fatigue cracks, reaches the predetermined number of cycles or other failure criteria, the test is stopped, the collected data is sorted and analyzed, and the fatigue performance test results of the blade are obtained.

[0045] The above description is only a preferred embodiment of the present utility model and is not intended to limit the present utility model. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present utility model should be included within the protection scope of the present utility model.

Claims

1. An aircraft blade fatigue testing fixture, comprising a clamping mechanism (3) for clamping engine blades, characterized in that: The clamping mechanism (3) is located on top of the base mechanism (2), and the base mechanism (2) is located on top of the base (1); The base mechanism (2) includes a positioning base (21) fixed at the top of the base (1) and a sliding base (22) that can adjust the clamping direction of the clamping mechanism (3). The sliding base (22) includes a second base (203) movably mounted on the top of the base (1), a positioning post (205) for limiting the clamp positioning frame (207), a clamp positioning frame (207) for supporting the clamping mechanism (3), and a limiting block (206) for stabilizing the clamp positioning frame (207). The limiting block (206) includes four sets. The limiting block (206) cooperates with the second base (203) to form a cross-shaped slot. The clamp positioning frame (207) can rotate 90° to adjust the installation direction of the clamping mechanism (3).

2. The aircraft blade fatigue testing fixture according to claim 1, characterized in that: The clamping mechanism (3) includes a first transverse clamp (31) set on the top of the positioning base (21), a second transverse clamp (32) set on the top of the sliding base (22), and a spare longitudinal clamp (33). The first transverse clamp (31), the second transverse clamp (32), and the longitudinal clamp (33) each include a second side plate (301) for fixing and installing the slide (302), a slide (302) for movably installing the clamping plate (304), and a bidirectional bolt rod (303) for driving the clamping plate (304) to clamp the blade. A secondary pressing rod (305) is threaded onto one side of the clamping plate (304). The secondary pressing rod (305) includes a screw, a spherical pressing block, and an internal hexagonal nut. The spherical pressing block is used to clamp the wavy groove at the root of the blade. An internal threaded slider (306) is fixedly connected to one side of the clamping plate (304). The internal threaded slider (306) is movably installed on one side of the slide (302).

3. The aircraft blade fatigue testing fixture according to claim 1, characterized in that: The positioning base (21) includes a first base (201) fixedly installed on the top of the base (1) and a first side plate (202) fixedly connected to the left and right sides of the first base (201). The first side plate (202) is used to fix the first transverse clamp (31).

4. The aircraft blade fatigue testing fixture according to claim 1, characterized in that: The top of the second base (203) is provided with a locking hole (204) for inserting the locking block at the bottom of the limiting block (206). The top of the fixture positioning frame (207) is provided with a limiting hole (208) for fixing the fixture positioning frame (207) in conjunction with the positioning column (205). A pad (209) is fixedly connected to one side of the fixture positioning frame (207) for connecting the output end of the fatigue testing machine.

5. A fatigue testing fixture for aircraft blades according to claim 1 or 2, characterized in that: The clamp positioning frame (207) has clamp mounting holes (310) on one side for fixing the second side plate (301) with bolts.

6. The aircraft blade fatigue testing fixture according to claim 2, characterized in that: The slides (302) inside the first transverse clamp (31) and the second transverse clamp (32) are arranged transversely, and the slides (302) inside the longitudinal clamp (33) are arranged longitudinally.

7. The aircraft blade fatigue testing fixture according to claim 1, characterized in that: The fixture positioning frame (207) can rotate to engage with any set of limit blocks (206) in the cross-shaped slot to achieve 90° interval angle positioning.

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