CN216350121U

CN216350121U - Aeroengine blade intensity detection device

Info

Publication number: CN216350121U
Application number: CN202122913322.3U
Authority: CN
Inventors: 聂金龙; 邢宇航; 高源�; 韩俊楠
Original assignee: Individual
Current assignee: Individual
Priority date: 2021-11-25
Filing date: 2021-11-25
Publication date: 2022-04-19
Anticipated expiration: 2031-11-25

Abstract

The utility model discloses a device for detecting the strength of an aircraft engine blade, which comprises a detector, a lens and a protection block, wherein the lens is positioned on the left side of the detector. Through setting up the camera lens, the protection piece, positioning mechanism and drive mechanism's cooperation is used, drive positioning mechanism through drive mechanism and remove to suitable position after, with protection piece and detector butt joint, loosen drive mechanism, positioning mechanism can fix the protection piece through the detector when reseing, the protection to the camera lens has been accomplished, it needs to carry out slight observation to the surface of blade through the camera lens to have solved current when detecting, and the camera lens exposes in the outside, also can't carry out fine protection to the camera lens under the condition that does not use the detector, the surface that leads to the camera lens very easily under the condition of placing for a long time is stained with a lot of slight dust, and the lens is concave inside the camera lens again, also be convenient for when having stained with and attached the dust and carry out abluent problem to the lens.

Description

Aeroengine blade intensity detection device

Technical Field

The utility model belongs to the technical field of blade detection of aero-generators, and particularly relates to a device for detecting the strength of an aero-engine blade.

Background

The detector is a device that can carry out hardness detection to aerogenerator's blade, and the problem that prior art exists is: the surface of the blade needs to be observed slightly through the lens during detection, the lens is exposed outside, the lens cannot be well protected under the condition that a detector is not used, the surface of the lens is easily stained with a lot of fine dust under the condition of long-term placement, the lens is concave inside the lens, and the lens is not convenient to use to clean when the dust is stained with.

SUMMERY OF THE UTILITY MODEL

Aiming at the problems in the prior art, the utility model provides a device for detecting the strength of an aircraft engine blade, which has the advantage of being convenient for protecting a lens, and solves the problems that the surface of the blade needs to be slightly observed through the lens during detection, the lens is exposed outside, the lens cannot be well protected under the condition of not using a detector, the surface of the lens is easily stained with a lot of fine dust under the condition of long-term placement, the lens is concave in the lens, and the lens is not convenient to use and clean when the lens is stained with dust.

The utility model is realized in such a way that the aero-engine blade strength detection device comprises a detector, a lens and a protection block, wherein the lens is positioned on the left side of the detector, the protection block is positioned on the left side of the lens, the surface on the right side of the protection block is in contact with the inner cavity of the detector, an accommodating groove is formed in the inner cavity of the protection block, a positioning mechanism matched with the protection block is arranged in the inner cavity of the accommodating groove, and a transmission mechanism matched with the positioning mechanism is arranged in the inner cavity of the accommodating groove.

Preferably, the positioning mechanism comprises two positioning rods, one side of each positioning rod opposite to the other side of each positioning rod is fixedly connected with the extrusion block, one side of each positioning rod opposite to the other side of each positioning rod is fixedly connected with the spring, and one side of each spring close to the inner wall of the corresponding accommodating groove is fixedly connected with the inner wall of the corresponding accommodating groove.

Preferably, the transmission mechanism comprises a movable block, connecting columns are fixedly connected to the top and the bottom of the front side of the movable block, the surface of each connecting column is in contact with the inner cavity of the extrusion block, and a transmission rod is fixedly connected to the front side of the movable block.

Preferably, the right side of the inner cavity of the accommodating groove is fixedly connected with a supporting plate, the top and the bottom of the supporting plate are fixedly connected with limiting blocks, the inner cavity of each limiting block is movably connected with a movable rod, and one side of each movable rod, which is close to the positioning rod, is fixedly connected with the positioning rod.

Preferably, the top and the bottom of the inner cavity of the protection block are both provided with connecting holes, the top and the bottom of the inner cavity of the detector are both provided with positioning grooves, and the opposite sides of the two positioning rods both penetrate through the connecting holes and extend to the inner cavity of the positioning grooves.

Preferably, the front side of the protection block is provided with a movable hole, and the front side of the transmission rod penetrates through the movable hole and extends to the front side of the protection block.

Compared with the prior art, the utility model has the following beneficial effects:

1. according to the utility model, through the matched use of the lens, the protection block, the positioning mechanism and the transmission mechanism, after the transmission mechanism drives the positioning mechanism to move to a proper position, the protection block is butted with the detector, the transmission mechanism is released, the positioning mechanism can fix the protection block through the detector while resetting, and the protection of the lens is completed, so that the problems that the surface of the blade needs to be slightly observed through the lens when in detection, the lens is exposed outside, the lens cannot be well protected under the condition that the detector is not used, the surface of the lens is easily adhered with a lot of fine dust under the condition of long-term placement, the lens is concave in the lens, and the lens is not convenient to clean when being adhered with dust are solved.

2. According to the utility model, the positioning rod plays a role in rapidly fixing the protective block through the detector by arranging the positioning mechanism, and the condition that the protective block cannot be fixed when the lens cover is arranged inside the protective block so as to fall off is avoided.

3. By arranging the transmission mechanism, the movable block plays a role in rapidly driving the two positioning rods to move through the connecting column and the extrusion block, and the situation that the protective block cannot be taken down when the lens needs to be used is avoided.

4. According to the utility model, the supporting plate, the limiting block and the movable rod are arranged, the supporting plate has the effect of limiting the positioning rod through the limiting block and the movable rod, and the situation that the positioning rod shakes in the moving process is avoided.

5. The positioning rod is provided with the connecting hole and the positioning groove, and the connecting hole plays a role in enabling the positioning rod to be rapidly in butt joint with the positioning groove.

6. The movable hole is arranged, so that the condition that the transmission rod is contacted with the inner wall of the protection block when moving to generate friction is avoided.

Drawings

FIG. 1 is a schematic diagram of a structure provided by an embodiment of the present invention;

FIG. 2 is a front cross-sectional view provided by an embodiment of the present invention;

FIG. 3 is an enlarged view of a portion of FIG. 1 at A in accordance with an embodiment of the present invention;

fig. 4 is a partial enlarged view of the embodiment of the present invention provided at B in fig. 2.

In the figure: 1. a detector; 2. a lens; 3. a protection block; 4. a receiving groove; 5. a positioning mechanism; 6. a transmission mechanism; 501. positioning a rod; 502. extruding the block; 503. a spring; 601. a movable block; 602. connecting columns; 603. a transmission rod; 7. a support plate; 8. a limiting block; 9. a movable rod; 10. connecting holes; 11. positioning a groove; 12. and (4) a movable hole.

Detailed Description

In order to further understand the contents, features and effects of the present invention, the following embodiments are illustrated and described in detail with reference to the accompanying drawings.

The structure of the present invention will be described in detail below with reference to the accompanying drawings.

As shown in fig. 1 to 4, the device for detecting the strength of the blade of the aircraft engine provided by the embodiment of the utility model comprises a detector 1, a lens 2 and a protection block 3, wherein the lens 2 is located on the left side of the detector 1, the protection block 3 is located on the left side of the lens 2, the surface on the right side of the protection block 3 is in contact with the inner cavity of the detector 1, an accommodating groove 4 is formed in the inner cavity of the protection block 3, a positioning mechanism 5 used in cooperation with the protection block 3 is arranged in the inner cavity of the accommodating groove 4, and a transmission mechanism 6 used in cooperation with the positioning mechanism 5 is arranged in the inner cavity of the accommodating groove 4.

Referring to fig. 4, the positioning mechanism 5 includes two positioning rods 501, a pressing block 502 is fixedly connected to one side of each of the two positioning rods 501 opposite to each other, a spring 503 is fixedly connected to one side of each of the two positioning rods 501 opposite to each other, and one side of the spring 503 close to the inner wall of the accommodating groove 4 is fixedly connected to the inner wall of the accommodating groove 4.

Adopt above-mentioned scheme: through setting up positioning mechanism 5, locating lever 501 has played the effect that can be quick fix protection piece 3 through detector 1, thereby has avoided protection piece 3 can't fix the condition that drops appear when inside with lens 2 cover.

Referring to fig. 4, the transmission mechanism 6 includes a movable block 601, a connection column 602 is fixedly connected to both the top and the bottom of the front side of the movable block 601, the surface of the connection column 602 is in contact with the inner cavity of the pressing block 502, and a transmission rod 603 is fixedly connected to the front side of the movable block 601.

Adopt above-mentioned scheme: through setting up drive mechanism 6, movable block 601 has played the effect that can be quick drives two locating levers 501 through spliced pole 602 and extrusion piece 502 and move, has avoided the condition that can't take off protection piece 3 when needs use camera lens 2.

Referring to fig. 4, the right side fixedly connected with backup pad 7 of holding groove 4 inner chamber, the equal fixedly connected with stopper 8 in top and the bottom of backup pad 7, the inner chamber swing joint of stopper 8 has movable rod 9, one side and locating lever 501 fixed connection that movable rod 9 is close to locating lever 501.

Adopt above-mentioned scheme: through setting up backup pad 7, stopper 8 and movable rod 9, backup pad 7 has played and can carry out spacing effect to locating lever 501 through stopper 8 and movable rod 9, has avoided locating lever 501 to appear the condition of rocking at the removal in-process.

Referring to fig. 4, connecting holes 10 have been all seted up to the top and the bottom of protection piece 3 inner chamber, and constant head tank 11 has all been seted up to the top and the bottom of detector 1 inner chamber, and the connecting hole 10 is all passed and the inner chamber that extends to constant head tank 11 to one side that two locating levers 501 are relative.

Adopt above-mentioned scheme: by providing the connecting hole 10 and the positioning groove 11, the connecting hole 10 plays a role in enabling the positioning rod 501 to be quickly butted against the positioning groove 11.

Referring to fig. 4, a movable hole 12 is opened at the front side of the protection block 3, and the front side of the driving rod 603 passes through the movable hole 12 and extends to the front side of the protection block 3.

Adopt above-mentioned scheme: by providing the movable hole 12, the movable hole 12 prevents the transmission rod 603 from contacting the inner wall of the protection block 3 when moving, thereby generating friction.

The working principle of the utility model is as follows:

when using, pulling transfer line 603, transfer line 603 can drive movable block 601 and remove, movable block 601 can drive extrusion block 502 through spliced pole 602 and remove when removing, extrusion block 502 can drive locating lever 501 and remove and advance the compression to spring 503 when removing, after locating lever 501 removed to suitable position, with protection piece 3 and the butt joint of camera lens 2 and make the right side of protection piece 3 insert the inner chamber at detector 1, loosen transfer line 603, the elasticity resilience of spring 503 can drive locating lever 501 and insert the inner chamber of constant head tank 11 and fix protection piece 3 through detector 1, the protection to camera lens 2 has been accomplished.

In summary, the following steps: the strength detection device for the blades of the aircraft engine is characterized in that through the matching use of the lens 2, the protection block 3, the positioning mechanism 5 and the transmission mechanism 6, after the transmission mechanism 6 drives the positioning mechanism 5 to move to a proper position, the protection block 3 is butted with the detector 1, the transmission mechanism 6 is loosened, the positioning mechanism 5 can fix the protection block 3 through the detector 1 while resetting, the protection of the lens 2 is completed, the problem that the surface of the blade needs to be slightly observed through the lens when the detection is carried out, and the lens is exposed outside in the prior art is solved, the lens cannot be well protected without using a detector, the surface of the lens is easily adhered with a lot of fine dust under the condition of long-term placement, the lens is concave in the lens, and the lens is not convenient to clean when being adhered with dust.

It is noted that, herein, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus.

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 utility model, the scope of which is defined in the appended claims and their equivalents.

Claims

1. The utility model provides an aeroengine blade intensity detection device, includes detector (1), camera lens (2) and protection piece (3), its characterized in that: lens (2) are located the left side of detector (1), protection piece (3) are located lens (2) left side, the surface on protection piece (3) right side contacts with the inner chamber of detector (1), the inner chamber of protection piece (3) has been seted up and has been accomodate groove (4), the inner chamber of accomodating groove (4) is provided with positioning mechanism (5) that use with protection piece (3) cooperation, the inner chamber of accomodating groove (4) is provided with drive mechanism (6) that use with positioning mechanism (5) cooperation.

2. An aircraft engine blade strength detection apparatus according to claim 1, wherein: positioning mechanism (5) include two locating levers (501), and equal fixedly connected with extrusion piece (502) in two locating levers (501) relative one side, equal fixedly connected with spring (503) in two locating levers (501) opposite one side, spring (503) are close to the one side of accomodating groove (4) inner wall and the inner wall fixed connection of accomodating groove (4).

3. An aircraft engine blade strength detection apparatus according to claim 2, wherein: the transmission mechanism (6) comprises a movable block (601), the top and the bottom of the front side of the movable block (601) are fixedly connected with a connecting column (602), the surface of the connecting column (602) is in contact with the inner cavity of the extrusion block (502), and the front side of the movable block (601) is fixedly connected with a transmission rod (603).

4. An aircraft engine blade strength detection apparatus according to claim 2, wherein: accomodate right side fixedly connected with backup pad (7) of groove (4) inner chamber, the top and the equal fixedly connected with stopper (8) in bottom of backup pad (7), the inner chamber swing joint of stopper (8) has movable rod (9), one side and locating lever (501) fixed connection that movable rod (9) are close to locating lever (501).

5. An aircraft engine blade strength detection apparatus according to claim 2, wherein: connecting hole (10) have all been seted up to the top and the bottom of protection piece (3) inner chamber, constant head tank (11) have all been seted up to the top and the bottom of detector (1) inner chamber, and connecting hole (10) are all passed and the inner chamber that extends to constant head tank (11) to two locating levers (501) relative one side.

6. An aircraft engine blade strength detection apparatus according to claim 3, wherein: the front side of the protection block (3) is provided with a movable hole (12), and the front side of the transmission rod (603) penetrates through the movable hole (12) and extends to the front side of the protection block (3).