Tool for aero-engine turbine blade high-temperature vibration test

Abstract

The utility model belongs to the field of tools, and particularly relates to a tool for a high-temperature vibration test of an aero-engine turbine blade, which comprises a test box, a box door is arranged at the front end of the test box, a support is fixedly connected to the lower end of the test box, a vibration mechanism is arranged on the test box, a support ring is arranged on the vibration mechanism, and the support ring is fixedly connected with the box door. A screw rod is fixedly connected to the upper end of the supporting ring, a screw tube is connected to the outer side of the screw rod through threads, a hanging plate is installed on the outer side of the screw tube through a bearing, and an electric heating ring is fixedly connected to the lower end of the hanging plate. According to the utility model, the motor drives the supporting shaft to drive the sliding cylinder to rotate, so that the inclined block slides relative to the stop block, the sliding cylinder drives the blade sleeved on the outer side of the adjusting rod to vibrate up and down, and the device can carry out a vibration test in the process of heating the blade.

Description

Technical Field

[0001] This utility model relates to the field of tooling technology, specifically to a tooling for high-temperature vibration testing of aero-engine turbine blades. Background Technology

[0002] Patent application CN119643311A discloses an experimental method for measuring the thermal stress characteristics of turbine cooling blades under high-temperature conditions. A specific proportion of alumina solution is sprayed as a speckle coating onto the blade surface. After a series of curing processes, images of the speckle under high temperature are captured using digital image correlation (DIC). Image registration technology is then used to calculate the displacement of each point on the blade surface, thereby estimating the strain and stress. This invention enables the experimental measurement of turbine blade strain under high-temperature conditions and allows the determination of turbine blade stress based on the stress-strain relationship. This invention provides technical support for turbine blade cooling and safety design.

[0003] However, the existing technology has certain shortcomings. The device only conducts high-temperature tests on the blades and cannot simultaneously test the impact of vibrations generated during the blades' operation on the blades. In addition, the high temperature experienced by the blades is not easy to control. Utility Model Content

[0004] The purpose of this invention is to provide a tooling for high-temperature vibration testing of aero-engine turbine blades, which solves the problems that the device can only perform high-temperature testing on the blades, but cannot simultaneously test the impact of vibration generated during the blades' operation on the blades, and that the high temperature experienced by the blades is difficult to control.

[0005] To achieve the above objectives, this utility model provides the following technical solution: a tooling for high-temperature vibration testing of aero-engine turbine blades, comprising a test chamber, a door at the front end of the test chamber, a support fixedly connected to the lower end of the test chamber, a vibration mechanism on the test chamber, a support ring on the vibration mechanism, a screw fixedly connected to the upper end of the support ring, a threaded tube connected to the outer side of the screw, a hanging plate mounted on the outer side of the threaded tube via a bearing, and an electric heating coil fixedly connected to the lower end of the hanging plate.

[0006] Preferably, the test chamber has a sliding connection to a suspension rod, which is fixedly connected to a suspension plate. The suspension rod guides the movement of the suspension plate.

[0007] Preferably, the vibration mechanism includes a motor, which is fixedly installed with the test chamber. The motor's shaft passes through the test chamber and is rotatably connected to it. A support shaft is fixedly connected to the upper end of the motor's shaft. A slide cylinder is slidably connected to the outer side of the support shaft. A slider is fixedly connected to the upper end of the support shaft, and the slider and slide cylinder are slidably connected. A spring is provided on the outer side of the support shaft. An adjusting rod is fixedly connected to the upper end of the slide cylinder. A pressure ring is threadedly connected to the outer side of the adjusting rod. A support rod is fixedly connected to the surface of the slide cylinder, and an inclined block is fixedly connected to the end of the support rod. The motor drives the support shaft to rotate the slide cylinder, which in turn causes the inclined block to slide relative to the stop block. This causes the slide cylinder to drive the blade sleeved on the outer side of the adjusting rod to vibrate up and down, allowing the device to perform vibration testing during the heating process of the blade.

[0008] Preferably, one end of the spring is fixedly connected to the slide cylinder, and the other end of the spring is fixedly connected to the slider. By providing the spring, the slide cylinder can be easily reset.

[0009] Preferably, a guide block is fixedly connected to the surface of the slider, and the guide block and the slide cylinder are slidably connected. By setting the guide block, relative rotation between the slider and the slide cylinder is prevented.

[0010] Preferably, a stop block is fixedly connected inside the test chamber, and the stop block and the inclined block are slidably connected. By setting the stop block and the inclined block to cooperate, the slide cylinder can move up and down.

[0011] Preferably, a protrusion is fixedly connected to the upper end of the inclined block, and the protrusion contacts the support ring. By providing the protrusion, the friction between the inclined block and the support ring is reduced.

[0012] Compared with the prior art, the beneficial effects of this utility model are as follows:

[0013] 1. This utility model uses a motor to drive the support shaft to rotate the slide cylinder, which in turn causes the inclined block to slide relative to the stop block. This causes the slide cylinder to drive the blade sleeved on the outside of the adjusting rod to vibrate up and down, thus enabling the device to perform vibration testing during the heating process of the blade.

[0014] 2. This utility model uses the rotation of the screw and the screw tube to make a threaded movement, thereby changing the distance between the support ring and the hanging plate. This allows the device to adjust the distance between the electric heating coil and the blade according to the testing requirements during use, thus avoiding excessive heating temperature that could damage the blade. Attached Figure Description

[0015] Figure 1 This is a perspective view of the overall structure of this utility model;

[0016] Figure 2 This utility model Figure 1 A three-dimensional view of the test chamber;

[0017] Figure 3 This utility model Figure 2 A cross-sectional view of the sliding cylinder;

[0018] Figure 4 This utility model Figure 2 Enlarged view of point A.

[0019] In the diagram: 1. Test chamber; 2. Chamber door; 3. Support; 4. Vibration mechanism; 5. Hanging rod; 6. Hanging plate; 7. Electric heating coil; 8. Screw tube; 9. Screw; 10. Support ring; 41. Motor; 42. Support shaft; 43. Slide cylinder; 44. Slider; 45. Guide block; 46. Spring; 47. Adjusting rod; 48. Pressure ring; 49. Support rod; 410. Inclined block; 411. Stop block; 412. Protrusion. Detailed Implementation

[0020] 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.

[0021] Please see Figures 1-4 A fixture for high-temperature vibration testing of aero-engine turbine blades includes a test chamber 1, a door 2 at the front end of the test chamber 1, a support 3 fixedly connected to the lower end of the test chamber 1, a vibration mechanism 4 on the test chamber 1, a support ring 10 on the vibration mechanism 4, a screw 9 fixedly connected to the upper end of the support ring 10, a threaded tube 8 connected to the outer side of the screw 9, a hanging plate 6 mounted on the outer side of the threaded tube 8 via a bearing, an electric heating coil 7 fixedly connected to the lower end of the hanging plate 6, and a slidable rod 5 inside the test chamber 1. The rod 5 and the hanging plate 6 are fixedly connected, and the movement of the hanging plate 6 is guided by the rod 5.

[0022] Please see Figures 1-4The vibration mechanism 4 includes a motor 41, which is fixedly installed with the test chamber 1. The rotating shaft of the motor 41 passes through the test chamber 1 and is rotatably connected to it. A support shaft 42 is fixedly connected to the upper end of the rotating shaft of the motor 41. A slide cylinder 43 is slidably connected to the outer side of the support shaft 42. A slider 44 is fixedly connected to the upper end of the support shaft 42. The slider 44 and the slide cylinder 43 are slidably connected. A guide block 45 is fixedly connected to the surface of the slider 44. The guide block 45 and the slide cylinder 43 are slidably connected. By setting the guide block 45, relative rotation between the slider 44 and the slide cylinder 43 is prevented. A spring 46 is set on the outer side of the support shaft 42. One end of the spring 46 is fixedly connected to the slide cylinder 43, and the other end of the spring 46 is fixedly connected to the slider 44. By setting the spring 46, the slide cylinder 43 can be easily reset. An adjusting rod 47 is fixedly connected to the upper end of the slide cylinder 43. A pressure ring 48 is threadedly connected to the outside of the slide cylinder 43. A support rod 49 is fixedly connected to the surface of the slide cylinder 43. An inclined block 410 is fixedly connected to the end of the support rod 49. A stop block 411 is fixedly connected inside the test chamber 1. The stop block 411 and the inclined block 410 are slidably connected. By setting the stop block 411 and the inclined block 410 to cooperate, the slide cylinder 43 can move up and down. A protrusion 412 is fixedly connected to the upper end of the inclined block 410. The protrusion 412 contacts the support ring 10. By setting the protrusion 412, the friction between the inclined block 410 and the support ring 10 is reduced. The motor 41 drives the support shaft 42 to drive the slide cylinder 43 to rotate, thereby causing the inclined block 410 to slide relative to the stop block 411. This allows the slide cylinder 43 to drive the blade sleeved on the outside of the adjusting rod 47 to vibrate up and down, so that the device can perform vibration testing during the heating process of the blade.

[0023] The specific implementation process of this utility model is as follows: In use, the hanging plate 6 is moved upward to change the distance between the hanging plate 6 and the slide cylinder 43. Then, the blade is sleeved on the adjusting rod 47. The pressure ring 48 and the adjusting rod 47 are manually rotated to make a threaded movement, so that the pressure ring 48 and the blade come into contact and clamp the blade. Then, the device is adjusted according to the heating requirements. The screw 9 and the screw tube 8 are manually rotated to make a threaded movement, so that the distance between the support ring 10 and the hanging plate 6 changes. Thus, when the device is in use, the distance between the electric heating coil 7 and the blade can be adjusted according to the test requirements to avoid the blade being damaged due to excessive heating temperature. Then, the motor 41 is started. The motor 41 drives the support shaft 42 to rotate. The support shaft 42 drives the slide cylinder 43 to rotate. The rotation of the slide cylinder 43 drives the inclined block 410 to move through the support rod 49, so that the inclined block 410 slides relative to the stop block 411. Thus, the slide cylinder 43 drives the blade sleeved on the outside of the adjusting rod 47 to vibrate up and down, so that the device can perform vibration tests during the heating of the blade.

[0024] Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A fixture for high-temperature vibration testing of aero-engine turbine blades, comprising a test chamber (1), characterized in that: The test chamber (1) is provided with a door (2) at the front end. The test chamber (1) is fixedly connected with a support (3) at the lower end. The test chamber (1) is provided with a vibration mechanism (4). The vibration mechanism (4) is provided with a support ring (10). The upper end of the support ring (10) is fixedly connected with a screw (9). The outer side of the screw (9) is connected with a threaded tube (8). The outer side of the threaded tube (8) is installed with a hanging plate (6) through a bearing. The lower end of the hanging plate (6) is fixedly connected with an electric heating coil (7).

2. The fixture for high-temperature vibration testing of aero-engine turbine blades according to claim 1, characterized in that: The test chamber (1) is internally slidably connected to a suspension rod (5), which is fixedly connected to a suspension plate (6).

3. The fixture for high-temperature vibration testing of aero-engine turbine blades according to claim 1, characterized in that: The vibration mechanism (4) includes a motor (41), which is fixedly installed with the test chamber (1). The rotating shaft of the motor (41) passes through the test chamber (1) and is rotatably connected to the test chamber (1). A support shaft (42) is fixedly connected to the upper end of the rotating shaft of the motor (41). A slide cylinder (43) is slidably connected to the outer side of the support shaft (42). A slider (44) is fixedly connected to the upper end of the support shaft (42). The slider (44) and the slide cylinder (43) are slidably connected. A spring (46) is provided on the outer side of the support shaft (42). An adjusting rod (47) is fixedly connected to the upper end of the slide cylinder (43). A pressure ring (48) is threadedly connected to the outer side of the adjusting rod (47). A support rod (49) is fixedly connected to the surface of the slide cylinder (43). An inclined block (410) is fixedly connected to the end of the support rod (49).

4. The fixture for high-temperature vibration testing of aero-engine turbine blades according to claim 3, characterized in that: One end of the spring (46) is fixedly connected to the slide cylinder (43), and the other end of the spring (46) is fixedly connected to the slider (44).

5. The fixture for high-temperature vibration testing of aero-engine turbine blades according to claim 3, characterized in that: A guide block (45) is fixedly connected to the surface of the slider (44), and the guide block (45) and the slide cylinder (43) are slidably connected.

6. The fixture for high-temperature vibration testing of aero-engine turbine blades according to claim 3, characterized in that: The test chamber (1) is fixedly connected to a stop block (411), and the stop block (411) and the inclined block (410) are slidably connected.

7. The fixture for high-temperature vibration testing of aero-engine turbine blades according to claim 3, characterized in that: The upper end of the inclined block (410) is fixedly connected to a protrusion (412), and the protrusion (412) is in contact with the support ring (10).

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