CN213847255U

CN213847255U - Aeroengine bearing fault diagnosis data acquisition device

Info

Publication number: CN213847255U
Application number: CN202023110935.5U
Authority: CN
Inventors: 石峰; 李琳; 闫保山
Original assignee: Individual
Current assignee: Individual
Priority date: 2020-12-22
Filing date: 2020-12-22
Publication date: 2021-07-30
Anticipated expiration: 2030-12-22

Abstract

The utility model discloses an aeroengine bearing failure diagnosis data acquisition device, comprising a main body, the main part outside is provided with the protective frame, both sides surface four corners department is all fixed and is provided with the block rubber about the protective frame, protective frame top inner wall is provided with the platform, and the joint groove has all been seted up on the platform surface to four sides inside the protective frame, four sides of main part outside are all fixed and are provided with first installing frame, first installing frame one side is the fixed second installing frame that is provided with all. The utility model discloses a place the structural style in the protective frame in the main part in can be so that if the unexpected collision takes place in the conventional use of this device, through placing the structural style in the protective frame in, including the interpolation of block rubber, rubber shock pad uses for the protective frame can be for the omnidirectional shock attenuation protection of main part, has effectively reduced the main part and has received the impact when colliding, and then has effectively increased the life of this device.

Description

Aeroengine bearing fault diagnosis data acquisition device

Technical Field

The utility model belongs to the technical field of bearing vibration test, concretely relates to aeroengine bearing failure diagnosis data acquisition device.

Background

The traditional bearing single-item test method is carried out on a bearing tester, and the tester comprises a main shaft driving device, a mandrel for mounting a bearing, an axial load loading device, a radial load loading device, a circulating oil supply system, a mounting rack of an acceleration sensor system and the like. Bearing quality is assessed by measuring the vibration velocity or acceleration level of the bearing at the bearing outer ring test point over a specified rotational speed.

At present, when the bearing fault diagnosis test is carried out through a bearing tester, corresponding data acquisition equipment which needs to be used acquires test data, the collecting device is small in multi-body type and simple in structure, the collecting device is easy to damage due to some external accidental collisions, the service cost of a user is increased while the service life of the collecting device is shortened, and the current use requirements of people cannot be met.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide an aeroengine bearing failure diagnosis data acquisition device to solve the problem that proposes among the above-mentioned background art.

In order to achieve the above object, the utility model provides a following technical scheme: an aeroengine bearing fault diagnosis data acquisition device comprises a main body, wherein a protective frame is arranged on the outer side of the main body, rubber blocks are fixedly arranged at four corners of the upper side surface and the lower side surface of the protective frame, a lapping table is arranged on the inner wall of the top end of the protective frame, clamping grooves are formed in the lapping table surface at four sides inside the protective frame, a first mounting frame is fixedly arranged at four sides outside the main body, a second mounting frame is fixedly arranged at one side of the first mounting frame, a rubber shock pad is arranged between the first mounting frame and the second mounting frame, a connecting mechanism is uniformly arranged at the outer side of the rubber shock pad between the first mounting frame and the second mounting frame, a connecting plate is arranged at one side of the second mounting frame, one end of the connecting plate is located inside the clamping groove, grooves are formed in the surface of one end, located inside the clamping groove, of the connecting plate at two sides inside the protective frame, the inside both sides of protective frame all seted up the draw-in groove in joint inslot portion one side, be provided with fixed establishment between recess and the draw-in groove.

Preferably, coupling mechanism includes movable groove, connecting rod and stopper, a plurality of movable grooves have evenly been seted up to first installing frame one end lateral wall inside, second installing frame one end lateral wall evenly is provided with a plurality of connecting rods, and is a plurality of the one end of connecting rod all is located the movable groove inside, and is a plurality of the movable groove inside all is fixed in the one end of a plurality of connecting rods and is provided with the stopper.

Preferably, the fixing mechanism comprises a first spring and a trapezoid clamping block, the first spring is mounted at one end inside the groove, the trapezoid clamping block is mounted at one end of the first spring inside the groove, and one end of the trapezoid clamping block is located inside the clamping groove.

Preferably, a limiting plate is arranged inside the groove and outside one end of the trapezoidal clamping block.

Preferably, the holding tank has all been seted up on draw-in groove one side to the outside both sides surface of protective frame, the inside both sides of protective frame all are provided with the push rod through the activity in the inside one end of draw-in groove, the one end of push rod is located inside the holding tank, the draw-in groove is inside all to be fixed in the one end of push rod and is provided with the push pedal, a side surface of push pedal all with the one end surface contact of trapezoidal fixture block, the holding tank is inside to be provided with in the one end of push rod is fixed and is pressed the piece.

Preferably, the second springs are installed on the two sides of the interior of the protection frame and at the bottom of the interior of the clamping groove, the stress plates are arranged on the top ends of the second springs, and the upper surfaces of the stress plates are in surface contact with one ends of the connecting plates.

Compared with the prior art, the beneficial effects of the utility model are that:

(1) the utility model discloses a place the structural style in the protective frame in the main part in can be so that if unexpected collision takes place in the conventional use of this device, place the structural style in the protective frame in through, including the block rubber, the interpolation of rubber shock pad is used, make the protective frame can be the omnidirectional shock attenuation protection of main part, the impact of main part when receiving the collision has effectively been reduced, and then effectively increased the life of this device, through the connecting plate, joint groove and fixed establishment's cooperation is used and can be made the interpolation work of main part in the protective frame can convenient and fast's completion, need not adopt too much appurtenance and installation procedure, and then effectively improved the convenience in use of the protective frame who adds.

(2) The utility model discloses a push rod, the push pedal, the cooperation of second spring and atress board is used can be convenient the separation work between completion main part and the protective frame, make to have between main part and the protective frame and be connected convenient advantage and still have the convenient advantage of separation simultaneously, thereby make the concrete application of protective frame have further convenience in use, the structural style that comes the holding to receive the piece through the holding tank still can prevent to receive the piece because of the unexpected condition that collides pressurized with trapezoidal fixture block break away from the draw-in groove, make through the push rod, the push pedal, the structure that is used for carrying out the separation such as second spring and atress board has better practical application effect.

Drawings

Fig. 1 is a schematic diagram of the overall structure of the device for collecting the fault diagnosis data of the bearing of the aero-engine of the present invention;

fig. 2 is a schematic view of an installation structure of the fixing mechanism of the aero-engine bearing fault diagnosis data acquisition device of the present invention;

fig. 3 is an enlarged schematic view of a point a in fig. 1 of the device for collecting data of diagnosing a bearing failure of an aircraft engine according to the present invention;

fig. 4 is an enlarged schematic view of B in fig. 2 of the utility model discloses an aeroengine bearing fault diagnosis data acquisition device.

In the figure: 1. a main body; 2. a protective frame; 3. a rubber block; 4. building a platform; 5. a clamping groove; 6. a first mounting frame; 7. a second mounting frame; 8. a rubber shock pad; 9. a connecting mechanism; 10. a connecting plate; 11. a groove; 12. a card slot; 13. a fixing mechanism; 14. a movable groove; 15. a connecting rod; 16. a limiting block; 17. a first spring; 18. a trapezoidal fixture block; 19. a limiting plate; 20. accommodating grooves; 21. a push rod; 22. pushing the plate; 23. a pressed block; 24. a second spring; 25. a stress plate.

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. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.

Please refer to fig. 1-4, the utility model provides an aeroengine bearing failure diagnosis data acquisition device, including main part 1, main part 1 outside is provided with protective frame 2, protective frame 2 upper and lower both sides surface four corners department all fixes and is provided with rubber block 3, protective frame 2 top inner wall is provided with takes platform 4, protective frame 2 inside four sides have all seted up joint groove 5 on taking platform 4 surface, 1 outside four sides of main part are all fixed and are provided with first installing

frame

6, 6 one side of first installing frame is all fixed and is provided with second installing frame 7, all be provided with rubber shock pad 8 between first installing frame 6 and the second installing frame 7, evenly be provided with coupling mechanism 9 in the rubber shock pad 8 outside between first installing frame 6 and the second installing frame 7, second installing frame 7 one side all is provided with connecting plate 10, the one end of connecting plate 10 all is located joint groove 5 inside, protective frame 2 inside both sides all set up flutedly at the connecting plate 10 one side surface that is located joint groove 5 inside 11, draw-in groove 12 has all been seted up to inside both sides of protective frame 2 in inside one side of joint groove 5, is provided with fixed establishment 13 between recess 11 and draw-in groove 12.

In this embodiment, it is preferred, coupling mechanism 9 includes movable groove 14, connecting rod 15 and stopper 16, a plurality of movable grooves 14 have evenly been seted up to 6 one end lateral walls of first installing frame, 7 one end lateral walls of second installing frame evenly are provided with a plurality of connecting rods 15, the one end of a plurality of connecting rods 15 all is located movable groove 14 inside, a plurality of movable grooves 14 are inside all fixed stopper 16 that is provided with in the one end of a plurality of connecting rods 15, accomplish the result of use between first installing frame 6 and the second installing frame 7 in order to guarantee rubber shock pad 8 through coupling mechanism 9.

In this embodiment, preferably, the fixing mechanism 13 includes a first spring 17 and a trapezoidal fixture block 18, the first spring 17 is all installed at the inside one end of the groove 11, the trapezoidal fixture block 18 is all installed at the inside one end of the first spring 17 of the groove 11, the one end of the trapezoidal fixture block 18 is all located inside the clamping groove 12, and the fixing mechanism 13 is used for fixing the connection between the main body 1 and the protection frame 2.

In this embodiment, preferably, a limiting plate 19 is disposed inside the groove 11 and outside one end of the trapezoidal latch 18, and the limiting plate 19 is used to prevent one end of the trapezoidal latch 18 from being separated from the groove 11.

In this embodiment, it is preferred, holding tank 20 has all been seted up on draw-in groove 12 one side on the outside both sides surface of protective frame 2, the inside both sides of protective frame 2 all are provided with push rod 21 through the activity in the inside one end of draw-in groove 12, the one end of push rod 21 is located inside holding tank 20, draw-in groove 12 is inside all fixed push pedal 22 that is provided with in the one end of push rod 21, a side surface of push pedal 22 all with trapezoidal fixture block 18's one end surface contact, holding tank 20 is inside to be provided with in the one end of push rod 21 is fixed and to be pressed piece 23, when needs take out main part 1 from the installing frame, the staff accessible is pressed simultaneously and is pressed pressure that pressed piece 23 makes push rod 21 drive push pedal 22 and pushes away trapezoidal fixture block 18 from draw-in groove 12.

In this embodiment, it is preferred, second spring 24 is all installed to the inside both sides of protective frame 2 in the inside bottom of joint groove 5, second spring 24 top all is provided with atress board 25, atress board 25 upper surface all with the one end surface contact of connecting plate 10, when trapezoidal fixture block 18 is pushed away from draw-in groove 12, the end department of connecting plate 10 can produce partial displacement under second spring 24's effort, can make trapezoidal fixture block 18 imbed again to draw-in groove 12 from this, then the staff only needs to take out main part 1 through simple carrying.

The utility model discloses a theory of operation and use flow: the main body 1 is a data acquisition device with the function of acquiring the fault diagnosis data of the bearing of the aeroengine, the data acquisition device can be connected with a bearing tester by using a wireless local area network to acquire the diagnosis data, the main body 1 is arranged in the protective frame 2, in the conventional use process of the device, if accidental collision occurs, the protective frame 2 can be subjected to all-directional shock absorption protection by adding the rubber block 3 and the rubber shock pad 8 through the structural form arranged in the protective frame 2, the collision force of the main body 1 when the main body 1 is collided is effectively reduced, the service life of the device is effectively prolonged, when the main body 1 is added in the protective frame 2, a user only needs to put the main body 1 into the protective frame 2 in a swinging manner, one end of the connecting plate 10 is aligned with the clamping groove 5, then the main body 1 can be put into the mounting frame, in the process, the inner wall of the clamping groove 5 can abut against the inclined surface of the trapezoid clamping block 18 to enable the trapezoid clamping block 18 to retract into the groove 11, when the groove 11 is aligned with the clamping groove 12, the trapezoid clamping block 18 can be embedded into the clamping groove 12 under the action of the first spring 17, so that the main body 1 can be fixed inside the mounting frame, at the moment, the fixed connecting plate 10 can abut against the stress plate 25 to enable the second spring 24 to be pressed, when the main body 1 needs to be taken out of the mounting frame, a worker needs to press the pressing pressure blocks 23 at two sides simultaneously to enable the push rod 21 to drive the push plate 22 to push the trapezoid clamping block 18 away from the clamping groove 12, at the moment, the end of the connecting plate 10 can generate partial displacement under the action of the second spring 24, so that the trapezoid clamping block 18 can not be embedded into the clamping groove 12 again, then the worker can take out the main body 1 only through simple lifting, when the rubber shock pad 8 is provided, due to the connecting structure of the connecting rod 15 and the movable groove 14 in the connecting mechanism 9, relative displacement can be produced between first installing frame 6 and the second installing frame 7, has guaranteed rubber shock pad 8's normal use promptly, has also guaranteed the joint strength between main part 1 and the installing frame simultaneously.

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

Claims

1. The utility model provides an aeroengine bearing failure diagnosis data acquisition device, includes main part (1), its characterized in that: the rubber shock absorber is characterized in that a protective frame (2) is arranged on the outer side of the main body (1), rubber blocks (3) are fixedly arranged at four corners of the upper side surface and the lower side surface of the protective frame (2), a lapping table (4) is arranged on the inner wall of the top end of the protective frame (2), clamping grooves (5) are formed in four sides of the inner portion of the protective frame (2) on the surface of the lapping table (4), first installation frames (6) are fixedly arranged on four sides of the outer portion of the main body (1), second installation frames (7) are fixedly arranged on one sides of the first installation frames (6), rubber shock absorbing pads (8) are arranged between the first installation frames (6) and the second installation frames (7), connecting mechanisms (9) are uniformly arranged on the outer sides of the rubber shock absorbing pads (8), a connecting plate (10) is arranged on one side of the second installation frames (7), one end of the connecting plate (10) is located inside the clamping grooves (5), the protective frame is characterized in that grooves (11) are formed in one side surface, located inside the clamping groove (5), of the two sides inside the protective frame (2) at the connecting plate (10), clamping grooves (12) are formed in one side inside the clamping groove (5) of the two sides inside the protective frame (2), and fixing mechanisms (13) are arranged between the grooves (11) and the clamping grooves (12).

2. The aeroengine bearing fault diagnosis data collection device of claim 1, wherein: coupling mechanism (9) are including activity groove (14), connecting rod (15) and stopper (16), a plurality of activity grooves (14) have evenly been seted up to first installing frame (6) one end lateral wall is inside, second installing frame (7) one end lateral wall evenly is provided with a plurality of connecting rods (15), and is a plurality of the one end of connecting rod (15) all is located activity groove (14) inside, and is a plurality of activity groove (14) inside is all fixed stopper (16) of being provided with in the one end of a plurality of connecting rods (15).

3. The aeroengine bearing fault diagnosis data collection device of claim 1, wherein: fixed establishment (13) include first spring (17) and trapezoidal fixture block (18), first spring (17) are all installed to the inside one end of recess (11), trapezoidal fixture block (18) are all installed to the inside one end at first spring (17) of recess (11), the one end of trapezoidal fixture block (18) all is located draw-in groove (12) inside.

4. The aeroengine bearing fault diagnosis data collection device of claim 3, wherein: and a limiting plate (19) is arranged in the groove (11) and outside one end of the trapezoidal clamping block (18).

5. The aeroengine bearing fault diagnosis data collection device of claim 3, wherein: holding tank (20) have all been seted up on draw-in groove (12) one side on the outside both sides surface of protective frame (2), the inside both sides of protective frame (2) all are provided with push rod (21) through the activity in the inside one end of draw-in groove (12), the one end of push rod (21) is located inside holding tank (20), draw-in groove (12) are inside all to be fixed in the one end of push rod (21) and are provided with push pedal (22), a side surface of push pedal (22) all with the one end surface contact of trapezoidal fixture block (18), holding tank (20) are inside to be provided with in the one end of push rod (21) is fixed and to be pressed piece (23).

6. The aeroengine bearing fault diagnosis data collection device of claim 1, wherein: second spring (24) are all installed to inside both sides of protective frame (2) in joint groove (5) inside bottom, second spring (24) top all is provided with atress board (25), atress board (25) upper surface all with the one end surface contact of connecting plate (10).