CN216791389U

CN216791389U - Aircraft engine blade frequency measurement tool with positioning mechanism

Info

Publication number: CN216791389U
Application number: CN202220373967.4U
Authority: CN
Inventors: 游云洪; 王勇; 刘伟军; 朱荣文; 游侠
Original assignee: Chengdu Hongxia Technology Co Ltd
Current assignee: Chengdu Hongxia Technology Co Ltd
Priority date: 2022-02-22
Filing date: 2022-02-22
Publication date: 2022-06-21
Anticipated expiration: 2032-02-22

Abstract

The utility model discloses an aircraft engine blade frequency measurement frock with positioning mechanism, including workstation, base and switch, the working chamber has been seted up to the side of base, the top of working chamber is provided with servo motor, servo motor's output runs through the workstation, servo motor's output is provided with first cylinder, the output of first cylinder is provided with puts the thing platform, put the annular a plurality of draw-in grooves of having evenly seted up of up end of thing platform. This application is through being provided with workstation, working chamber, servo motor, limiting plate, a spacing section of thick bamboo, first cylinder, put thing platform, draw-in groove, support column, vibration pickup, oscilloscope, switch, data line, first splint, second cylinder, third splint and base structure, compares with prior art, puts the centre gripping that thing platform goes up and down and second cylinder control blade through first cylinder control, and this application can improve blade frequency measuring efficiency.

Description

Aircraft engine blade frequency measurement tool with positioning mechanism

Technical Field

The utility model relates to an aircraft engine blade processing technology field especially relates to an aircraft engine blade frequency measurement frock with positioning mechanism.

Background

During the operation of the blades of the aircraft engine, the vibration characteristics of the blades are poor, so that the damage accidents of the blades can be caused, the vibration frequency of the blades needs to be detected, the conventional blade frequency measurement is mainly carried out manually one by one, and the measurement efficiency is low.

SUMMERY OF THE UTILITY MODEL

This neotype aim at: in order to solve the problems, the invention provides an aircraft engine blade frequency measuring tool with a positioning mechanism.

In order to realize the purpose, the novel device adopts the following technical scheme:

the utility model provides an aircraft engine blade frequency measurement frock with positioning mechanism, includes workstation, base and switch, the working chamber has been seted up to the side of base, the top in working chamber is provided with servo motor, servo motor's output runs through the workstation, servo motor's output is provided with first cylinder, the output of first cylinder is provided with puts the thing platform, put the annular a plurality of draw-in grooves of evenly having seted up of up end of thing platform, the side of putting the thing platform is provided with frequency measurement mechanism.

Preferably, the frequency measuring mechanism comprises a support column, a vibration pickup is arranged at the top of the support column, an oscilloscope is arranged on the side surface of the support column, the oscilloscope is connected with the vibration pickup through a data line, and a clamping device is arranged on the side surface of the vibration pickup.

Preferably, clamping device includes first splint and second splint, the top side of second splint is provided with the second cylinder, the output of second cylinder is provided with the third splint.

Preferably, the up end of workstation is provided with the limiting plate, the up end of limiting plate is provided with spacing section of thick bamboo, servo motor's output shaft pass spacing section of thick bamboo and with spacing section of thick bamboo rotates the connection.

In conclusion, due to the adoption of the technical scheme, the novel beneficial effects are as follows:

this application is through being provided with workstation, working chamber, servo motor, limiting plate, a spacing section of thick bamboo, first cylinder, put thing platform, draw-in groove, support column, vibration pickup, oscilloscope, switch, data line, first splint, second cylinder, third splint and base structure, compares with prior art, puts the centre gripping that thing platform goes up and down and second cylinder control blade through first cylinder control, and this application can improve blade frequency measuring efficiency.

Drawings

Fig. 1 illustrates a schematic top view of a structure provided in accordance with an embodiment of the present invention;

fig. 2 illustrates a schematic diagram providing a front view configuration in accordance with the novel embodiment;

fig. 3 shows an enlarged schematic structural diagram at a in fig. 1 according to the present novel embodiment.

Illustration of the drawings:

1. a work table; 2. a working chamber; 3. a servo motor; 4. a limiting plate; 5. a limiting cylinder; 6. a first cylinder; 7. a placing table; 8. a card slot; 9. a support pillar; 10. a vibration pickup; 11. an oscilloscope; 12. a switch; 13. A data line; 14. a first splint; 15. a second splint; 16. a second cylinder; 17. a third splint; 18. a base.

Detailed Description

The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments of the present invention without any inventive step, are within the scope of the present invention.

Referring to fig. 1-3, the present invention provides a technical solution:

the utility model provides an aircraft engine blade frequency measurement frock with positioning mechanism, comprises a workbench 1, base 18 and switch 12, working chamber 2 has been seted up to base 18's side, the top of working chamber 2 is provided with servo motor 3, servo motor 3's output runs through workstation 1, servo motor 3's output is provided with first cylinder 6, the output of first cylinder 6 is provided with puts thing platform 7, put the annular a plurality of draw-in grooves 8 of having evenly seted up of the up end of thing platform 7, the side of putting thing platform 7 is provided with frequency measurement mechanism. The frequency measuring mechanism comprises a support column 9, a vibration pickup 10 is arranged at the top of the support column 9, an oscilloscope 11 is arranged on the side surface of the support column 9, the oscilloscope 11 is connected with the vibration pickup 10 through a data line 13, and a clamping device is arranged on the side surface of the vibration pickup 10. The clamping device comprises a first clamping plate 14 and a second clamping plate 15, a second air cylinder 16 is arranged on the top side of the second clamping plate 15, and a third clamping plate 17 is arranged at the output end of the second air cylinder 16. The upper end face of workstation 1 is provided with limiting plate 4, and the up end of limiting plate 4 is provided with a spacing section of thick bamboo 5, and servo motor 3's output shaft passes a spacing section of thick bamboo 5 and rotates with a spacing section of thick bamboo 5 and be connected.

Specifically, as shown in fig. 1 and 3, the frequency measuring mechanism includes a support column 9, a vibration pickup 10 is disposed on the top of the support column 9, an oscilloscope 11 is disposed on the side of the support column 9, the oscilloscope 11 is connected to the vibration pickup 10 through a data line 13, a clamping device is disposed on the side of the vibration pickup 10, the clamping device includes a first clamping plate 14 and a second clamping plate 15, a second cylinder 16 is disposed on the top side of the second clamping plate 15, and a third clamping plate 17 is disposed at the output end of the second cylinder 16.

Specifically, as shown in fig. 2, a limiting plate 4 is arranged on the upper end surface of the workbench 1, a limiting cylinder 5 is arranged on the upper end surface of the limiting plate 4, and an output shaft of the servo motor 3 penetrates through the limiting cylinder 5 and is rotatably connected with the limiting cylinder 5.

In conclusion, the aircraft engine blade frequency measuring tool with the positioning mechanism provided by the embodiment is in operation, firstly, the blade to be measured is placed in the clamping groove 8, the servo motor 3 is started to control the object placing table 7 to rotate, when the blade rotates to the lower side of the first clamping plate 14, the first air cylinder 6 is started to lift the object placing table 7, the blade falls between the first clamping plate 14 and the third clamping plate 17, the second air cylinder 16 is started to clamp the blade, then the object placing table 7 falls, the blade is separated from the clamping groove 8, and then the frequency test is performed.

The previous description of the embodiments is provided to enable any person skilled in the art to make or use the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the invention. Thus, the present invention is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. The utility model provides an aircraft engine blade frequency measurement frock with positioning mechanism, includes workstation (1), base (18) and switch (12), its characterized in that, working chamber (2) have been seted up to the side of base (18), the top of working chamber (2) is provided with servo motor (3), servo motor (3) output runs through workstation (1), servo motor (3) output is provided with first cylinder (6), the output of first cylinder (6) is provided with puts thing platform (7), put the up end annular of thing platform (7) and evenly seted up a plurality of draw-in grooves (8), the side of putting thing platform (7) is provided with frequency measurement mechanism.

2. The tool with the positioning mechanism for measuring the frequency of the aircraft engine blade according to claim 1, wherein the frequency measuring mechanism comprises a supporting column (9), a vibration pickup (10) is arranged at the top of the supporting column (9), an oscilloscope (11) is arranged on the side surface of the supporting column (9), the oscilloscope (11) is connected with the vibration pickup (10) through a data line (13), and a clamping device is arranged on the side surface of the vibration pickup (10).

3. The tool with the positioning mechanism for measuring the frequency of the blades of the aircraft engine is characterized in that the clamping device comprises a first clamping plate (14) and a second clamping plate (15), a second air cylinder (16) is arranged on the top side of the second clamping plate (15), and a third clamping plate (17) is arranged at the output end of the second air cylinder (16).

4. The tool with the positioning mechanism for measuring the blade frequency of the aircraft engine is characterized in that a limiting plate (4) is arranged on the upper end face of the workbench (1), a limiting barrel (5) is arranged on the upper end face of the limiting plate (4), and an output shaft of the servo motor (3) penetrates through the limiting barrel (5) and is rotatably connected with the limiting barrel (5).