Vibration testing device for blade disc of aero-engine

Abstract

The utility model discloses an aero-engine bladed disc vibration testing device which comprises a vibration table, a base is installed on the vibration table, a bottom cover is arranged on the base, top covers are symmetrically arranged on the upper side of the bottom cover, the top covers and the bottom cover are matched to fix a blisk, and a plurality of connecting rod pieces are arranged on the base. The utility model relates to the technical field of aero-engine testing devices, and the aero-engine bladed disc vibration testing device meets the requirements of vibration testing tests of blisk with different specifications by replacing a bottom cover and a top cover which are matched with the blisk in size, thereby greatly relieving the problems that the vibration testing tests of the blisk are time-consuming and labor-consuming, the cost is high, and the testing efficiency is high. According to the technical scheme, the problems that in the replacement process, opposite pulling of the top cover and the bottom cover can be conveniently operated through the positioning installer to achieve fixation of the blisk, and meanwhile the multiple screws are installed in a distributed mode, so that the blisk is pressed and fixed more stably and evenly.

Description

Technical Field

[0001] The utility model relates to the technical field of aero-engine testing devices, in particular to an aero-engine blade disk vibration testing device. Background Art

[0002] In the application process of aircraft engines, the integral blade disk is the core component of the new generation of aircraft engines. The vibration fatigue failure problem of the integral blade disk is very prominent. Therefore, it is necessary to test the dynamic characteristics of the integral blade disk through vibration test to avoid fatigue damage of the integral blade disk due to vibration.

[0003] For example, publication number CN211477553U discloses a vibration test device for an integral blade disc of an aero-engine. By replacing the bottom cover and the top cover that match the size of the integral blade disc, the vibration test requirements of the integral blade disc of different specifications can be met, which greatly alleviates the problem that the vibration test of the integral blade disc is time-consuming, labor-intensive, costly, and has low test efficiency. However, bolts are used as connecting parts during the replacement process. During operation, the top cover and the bottom cover must cooperate to clamp the integral blade disc. However, this threaded rod structure only has a central force to squeeze the top cover. The force point is only in the center, and the center of the integral blade disc is prone to deviation, affecting the detection accuracy of the aero-engine blade disc. In view of this, in-depth research was conducted on the above-mentioned problem, and thus this case was created. Utility Model Content

[0004] In view of the deficiencies of the prior art, the present invention provides an aero-engine blade disk vibration test device, which solves the problems of the prior art.

[0005] To achieve the above objectives, the present invention is implemented through the following technical solutions: an aero-engine blade disk vibration test device, comprising a vibration table, a base mounted on the vibration table, a bottom cover provided on the base, a top cover symmetrically provided on the upper side of the bottom cover, the top cover and the bottom cover cooperate to fix the entire blade disk, and a plurality of connecting rods are provided on the base;

[0006] The plurality of connecting rods are arranged in a ring array and pass through the bottom cover, the top cover is provided with a plurality of connecting holes corresponding to the plurality of connecting rods, and a positioning mount is provided on one side of the top cover;

[0007] The positioning mount includes a sleeve plate, the sleeve plate is sleeved on a plurality of connecting rods, a plurality of rotating nuts are movably mounted on the sleeve plate, a plurality of transfer gears are sleeved on the plurality of rotating nuts, a movable seat is provided at the center of the sleeve plate, an adjustment main wheel is movably mounted on the movable seat, and the adjustment main wheel is engaged with the plurality of transfer gears;

[0008] A plurality of the rotating nuts are threadedly connected to a plurality of connecting rods, and the plurality of the rotating nuts push back the sleeve plates, and the sleeve plates are pressed onto the top cover.

[0009] Preferably, the base is fixed to the vibration table by a plurality of bolts arranged in a circular array.

[0010] Preferably, the head ends of the plurality of connecting rods are all sloped structures.

[0011] Preferably, the sizes of the bottom cover and the top cover match the inner diameter of the blisk.

[0012] Preferably, the bottom surface of the sleeve plate is provided with a plurality of contact seats, and the top surface of the top cover is provided with a plurality of through holes in a ring array, and the plurality of through holes are matched with the plurality of contact seats for limiting positions.

[0013] Preferably, the adjusting main wheel includes an adjusting knob, the adjusting knob is movably mounted on the movable seat, and the outer sleeve of the adjusting knob is provided with a driving gear that meshes with a plurality of transfer gears.

[0014] Beneficial effects

[0015] The utility model provides an aero-engine blisk vibration test device. The device has the following beneficial effects: The aero-engine blisk vibration test device can meet the vibration test requirements of blisks of different specifications by replacing the bottom cover and top cover that match the size of the blisk, greatly alleviating the time-consuming, labor-intensive, high-cost, and low-testing efficiency problems of blisk vibration testing. During the replacement process, the top cover and bottom cover can be easily pulled against each other by a positioning installer to secure the blisk. At the same time, multiple screws are installed in a distributed manner, providing a more stable and balanced compression fixation of the blisk. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 The present invention is a schematic diagram of the three-dimensional structure of an aero-engine blade disk vibration testing device.

[0017] Figure 2 The utility model is a schematic cross-sectional view of an aero-engine blade disk vibration test device.

[0018] Figure 3 The present invention is a schematic diagram of the explosion structure of an aero-engine blade disk vibration test device.

[0019] In the figure: 1. Vibration table; 2. Base; 3. Bottom cover; 4. Top cover; 5. Integral blade; 6. Connecting rod; 7. Positioning installer; 71. Sleeve plate; 72. Rotating nut; 73. Transfer gear; 74. Movable seat; 75. Contact seat; 76. Adjustment knob; 77. Driving gear. DETAILED DESCRIPTION

[0020] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the embodiments described are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0021] See also Figure 1-3 The present invention provides an implementation scheme: when performing a vibration test on the integral blade disk 5 of an aircraft engine, when using the test device described in the disclosed patent, the threaded rod structure that fixes the integral blade disk 5 only exerts force at the center to squeeze the top cover 4. The force point is only at the center, and the center of the integral blade disk 5 is easily deviated, affecting the detection accuracy of the aircraft engine blade disk.

[0022] According to the instruction manual Figure 1-3 It can be seen that in response to the above problems, the present application discloses an aero-engine blade disk vibration test device, including a vibration table 1, a vibration controller is provided on the vibration table 1, and different vibration intensities and frequencies are generated by the vibration controller, and then a base 2 is installed on the vibration table 1, and the base 2 plays the role of supporting and transmitting vibration, and a bottom cover 3 is provided on the base 2. A top cover 4 is symmetrically provided on the upper side of the bottom cover 3, and the top cover 4 cooperates with the bottom cover 3 to fix the entire blade disk 5. The bottom cover 3 transmits the vibration of the vibration table 1 to vibrate the entire blade disk 5, and a plurality of connecting rods 6 are provided on the base 2, and the top cover 4 and the bottom cover 3 are reversely pulled and fixed by using the plurality of connecting rods 6 as multiple connection points;

[0023] Specifically, according to the instructions Figure 1-3 It can be seen that the aforementioned connecting rods 6 are arranged in a ring array and pass through the bottom cover 3. The top cover 4 is provided with a plurality of connecting holes corresponding to the connecting rods 6. A positioning mounter 7 is provided on one side of the top cover 4. The top cover 4 is pulled back and fixed to the bottom cover 3 by the positioning mounter 7. The integral blade disk 5 to be inspected is placed between the bottom cover 3 and the top cover 4. The positioning mounter 7 is fixedly installed.

[0024] According to the instruction manual Figure 1-3 It can be seen that the positioning and mounting device includes a sleeve plate 71, which is sleeved on the plurality of connecting rods 6. A plurality of rotating nuts 72 are movably mounted on the sleeve plate 71, and a plurality of transfer gears 73 are sleeved on the plurality of rotating nuts 72. A movable seat 74 is provided at the center of the sleeve plate 71, and an adjusting main wheel is movably mounted on the movable seat 74, which meshes with the plurality of transfer gears 73.

[0025] During the specific implementation process, a number of selection holes are provided on the sleeve plate 71 corresponding to the number of connecting rods 6, and a number of rotating nuts 72 are movably assembled in the number of selection holes. The number of rotating nuts 72 are threadedly connected to the number of connecting rods 6. By adjusting the main wheel to link the number of transfer gears 73 to rotate, the number of rotating nuts 72 rotate synchronously, and then the number of rotating nuts 72 are threadedly connected to the number of connecting rods 6, so that the number of rotating nuts 72 push back the sleeve plate 71, and the sleeve plate 71 is pressed onto the top cover 4. There are several corresponding sleeve plates 71 on the top cover 4.

[0026] As a preferred solution, further, the base 2 is fixed to the vibration table 1 by a plurality of bolts arranged in a ring array, and the base 2 plays the role of supporting the bottom shell and its upper structure and transmitting vibration.

[0027] As a preferred solution, further, the head ends of the plurality of connecting rods 6 are all sloped structures, so as to facilitate the rotation of the nut 72 into the connecting rod 6 .

[0028] As a preferred solution, further, the sizes of the bottom cover 3 and the top cover 4 match the inner diameter of the integral blade disk 5, so that the centers of the bottom cover 3 and the top cover 4 can be mutually limited.

[0029] As a preferred solution, further, the bottom surface of the sleeve 71 is provided with a plurality of contact seats 75, and the top surface of the top cover 4 is provided with a plurality of through holes in a ring array, and the plurality of through holes are matched with the plurality of contact seats 75 for limiting, and the plurality of through holes are correspondingly limited with the plurality of contact seats 75, and the contact seats 75 play a limiting and guiding role for the through holes.

[0030] As a preferred solution, further, the adjustment main wheel includes an adjustment knob 76, and the adjustment knob 76 is movably mounted on the movable seat 74. The outer sleeve of the adjustment knob 76 is provided with a driving gear 77 that engages with several transfer gears 73. The adjustment knob 76 synchronously drives the driving gear 77 to rotate, which is also convenient for users to operate.

[0031] From the above, it can be seen that the aircraft engine blade disk vibration test device meets the requirements of vibration test of integral blade disks 5 of different specifications by replacing the bottom cover 3 and the top cover 4 that match the size of the integral blade disk 5, which greatly alleviates the problems of time-consuming, labor-intensive, high-cost and low test efficiency of the vibration test of the integral blade disk 5. During the replacement process, the positioning installer can conveniently operate the pulling of the top cover 4 and the bottom cover 3 to fix the integral blade disk 5. At the same time, multiple screws are installed in a distributed manner to provide a more stable and balanced compression of the integral blade disk 5.

[0032] Although the 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 variations may be made to these embodiments without departing from the principles and spirit of the present invention, and the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. An aero-engine blade disk vibration test device, comprising a vibration table (1), a base (2) mounted on the vibration table (1), a bottom cover (3) disposed on the base (2), a top cover (4) symmetrically disposed on the upper side of the bottom cover (3), the top cover (4) and the bottom cover (3) cooperating to fix the integral blade disk (5), characterized in that: A plurality of connecting rods (6) are provided on the base (2); The plurality of connecting rods (6) are arranged in a ring array and pass through the bottom cover (3); the top cover (4) is provided with a plurality of connecting holes corresponding to the plurality of connecting rods (6); and a positioning mount (7) is provided on one side of the top cover (4); The positioning mounter comprises a sleeve plate (71), the sleeve plate (71) is sleeved on a plurality of connecting rods (6), a plurality of rotating nuts (72) are movably mounted on the sleeve plate (71), a plurality of transfer gears (73) are sleeved on the plurality of rotating nuts (72), a movable seat (74) is provided at the center of the sleeve plate (71), an adjusting main wheel is movably mounted on the movable seat (74), and the adjusting main wheel is meshed with the plurality of transfer gears (73); The plurality of rotating nuts (72) are threadedly connected to the plurality of connecting rods (6), and the plurality of rotating nuts (72) push the sleeve plate (71) in reverse, and the sleeve plate (71) is pressed onto the top cover (4).

2. The aero-engine blade disk vibration testing device according to claim 1, characterized in that: The base (2) is fixed on the vibration table (1) by a plurality of bolts arranged in a ring array.

3. The aero-engine blade disk vibration testing device according to claim 2, characterized in that: The head ends of the plurality of connecting rods (6) are all sloped structures.

4. The aero-engine blade disk vibration testing device according to claim 3, characterized in that: The sizes of the bottom cover (3) and the top cover (4) match the inner diameter of the integral blade disk (5).

5. The aero-engine blade disk vibration testing device according to claim 4, characterized in that: The bottom surface of the sleeve plate (71) is provided with a plurality of contact seats (75), and the top surface of the top cover (4) is provided with a plurality of through holes in a ring array, and the plurality of through holes are matched with the plurality of contact seats (75) for limiting positions.

6. The aero-engine blade disk vibration testing device according to claim 5, characterized in that: The regulating main wheel comprises an regulating knob (76), the regulating knob (76) is movably mounted on the movable seat (74), and the regulating knob (76) is provided with a driving gear (77) on its outer sleeve and meshes with a plurality of transfer gears (73).

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