CN211824946U

CN211824946U - Fatigue-resistant detection clamp for aircraft engine blade

Info

Publication number: CN211824946U
Application number: CN202020865034.8U
Authority: CN
Inventors: 吴祖峰
Original assignee: Guizhou Lifeng Technology Co ltd
Current assignee: Guizhou Lifeng Technology Co ltd
Priority date: 2020-05-21
Filing date: 2020-05-21
Publication date: 2020-10-30
Anticipated expiration: 2030-05-21

Abstract

The utility model discloses an aircraft engine blade is able to bear or endure fatigue detection anchor clamps relates to aircraft engine blade production frock technical field, this aircraft engine blade is able to bear or endure fatigue detection anchor clamps, including fixing base and slide, sliding connection has the slider on the slide, all be provided with the chuck on slider and the fixing base, the bottom of chuck is provided with logical groove, two the chuck to the opposite double-layered groove that all is provided with turbine fan blade shape looks adaptation, the top and the bottom of pressing from both sides inslot wall all are provided with the grip block, and lie in the face that deviates from of two grip blocks on the same vertical line and all be provided with the extrusion ram. The utility model discloses a set up double-layered groove, grip block, fixed axle one, fixed axle two, movable block and turn buckle, solved aircraft engine blade fatigue-resistant testing in-process, to the centre gripping alone of blade one end, the blade other end causes the amplitude by inertia to be greater than the amplitude of anchor clamps one end, causes the not hard up problem of anchor clamps centre gripping easily.

Description

Fatigue-resistant detection clamp for aircraft engine blade

Technical Field

The utility model relates to an aircraft engine blade production frock technical field specifically is an aircraft engine blade is able to bear or endure fatigue detection anchor clamps.

Background

Fatigue is called as a fatal killer of mechanical parts, according to statistics, a large proportion of damage of the mechanical parts is caused by fatigue, according to different data sources and statistical methods, the common proportion is 40% to 90%, and an airplane as a vehicle has the absolute advantage of high speed, so that the airplane has irreplaceable effect in the current society, and due to the high-speed characteristic of the airplane, the production process and quality requirements of the parts are extremely strict in the production process of the airplane. The aircraft engine belongs to a main component of an aircraft flight power system, the main components of the aircraft engine are various blades, and the fatigue resistance of the blades directly influences the safety of the aircraft in the working process, so that the fatigue resistance detection is absolutely indelible before delivery. When the airplane fan blade is subjected to fatigue detection, the fan blade is clamped and fixed by a clamp, and the test detection is carried out by fatigue detection equipment such as a vibration table, so that the condition that the airplane fan blade can be delivered from a factory to meet the quality standard requirement is ensured.

In the fatigue-resistant testing process of present aircraft engine blade, anchor clamps are usually to the independent centre gripping of blade one end, because equipment itself just vibrates the work, the blade other end causes the amplitude to be greater than the amplitude of anchor clamps one end by inertia, causes the anchor clamps centre gripping not hard up easily, has the defect.

SUMMERY OF THE UTILITY MODEL

Technical problem to be solved

The utility model provides a not enough to prior art, the utility model provides an aircraft engine blade is able to bear or endure fatigue and detects anchor clamps has solved the aircraft engine blade and has able to bear or endure fatigue the testing process in, to the independent centre gripping of blade one end, the blade other end causes the amplitude to be greater than the amplitude of anchor clamps one end by inertia, causes the not hard up problem of anchor clamps centre gripping easily.

(II) technical scheme

In order to achieve the above object, the utility model provides a following technical scheme: a fatigue-resistant detection clamp for an aircraft engine blade comprises a fixed seat and a slide seat, wherein a slide block is connected to the slide seat in a sliding manner, chucks are arranged on the slide block and the fixed seat, a through groove is formed in the bottom of each chuck, clamping grooves matched with the shapes of turbine blades are formed in the two chucks in opposite directions, clamping blocks are arranged at the top and the bottom of the inner wall of each clamping groove, extrusion rods are arranged on the deviating surfaces of the two clamping blocks on the same vertical line, movable rods are rotatably connected to the top of each chuck and the top of the inner wall of the through groove, the extrusion rods penetrate through the chucks and are movably sleeved on the surfaces of the movable rods, a locking device is arranged between the two movable rods corresponding to the chucks, a first fixed shaft is arranged on the front surface and the back surface of the inner wall of the through groove, the end part of the first fixed shaft is rotatably connected with the movable, the inside of through-hole is vertical to be provided with fixed axle two, the surperficial activity of fixed axle two has cup jointed turn buckle bolt, the movable block passes through fixed axle two and turns to be connected with turn buckle bolt.

Preferably, the sliding seat is provided with a sliding groove matched with the sliding block in shape, and the surface of the sliding block is connected with the inner wall of the sliding groove in a sliding mode.

Preferably, the extrusion pole is including the first extrusion pole that is located turbine fan blade top and the second extrusion pole that is located turbine fan blade below, the position department that first extrusion pole is close to the top is provided with the perforation, the bottom of second extrusion pole is provided with the draw-in groove, first extrusion pole cup joints the surface at the movable rod through the perforation, the two-way draw-in groove joint of extrusion pole is on the surface of movable rod.

Preferably, locking device includes U-shaped pole, internal thread pipe, screw rod, dog and hand wheel, U-shaped pole and internal thread pipe fixed connection respectively are at the tip that corresponds two movable rods of same chuck, and the internal thread pipe is located the top of U-shaped pole, screw rod and internal thread pipe threaded connection, dog and hand wheel fixed connection respectively are at the bottom and the top of screw rod.

(III) advantageous effects

The utility model provides an aircraft engine blade is able to bear or endure fatigue detection anchor clamps possesses following beneficial effect:

the utility model has the advantages that the clamping groove, the clamping block, the first fixed shaft, the second fixed shaft, the movable block and the turn buckle are arranged, the screw rod and the turn buckle both have the screw thread self-locking function through threaded connection, the clamping block and the clamping groove are the same as the two ends of the fixed turbine fan blade, the distance between the two chucks can be adjusted by rotating the turn buckle, the turbine fan blade is convenient to install and disassemble, the two chucks can be pulled to avoid the looseness between the chucks and the turbine fan blade, the turn buckle can rotate up and down around the first fixed shaft and rotate back and forth around the second fixed shaft by the first fixed shaft and the second fixed shaft, so that the stable clamping effect on the two ends of the fan blade can still be ensured under the condition of amplitude difference between the two ends of the fan blade during vibration detection, the whole operation is simple, the use is convenient, the stable clamping effect is simultaneously realized, the problem, the other end of the blade is larger than the amplitude of one end of the clamp due to inertia, so that the clamp is easy to clamp and loosen.

Drawings

FIG. 1 is a schematic view of the overall structure of the present invention;

FIG. 2 is a front sectional view of the present invention;

FIG. 3 is a side sectional view of the slider of the present invention;

fig. 4 is a top sectional view of the U-shaped rod of the present invention.

In the figure: 1. a fixed seat; 2. a slide base; 3. a slider; 4. a chuck; 5. a through groove; 6. turbine blades; 7. a clamping groove; 8. a clamping block; 9. an extrusion stem; 91. a first extrusion rod; 92. a second extrusion rod; 93. perforating; 94. a card slot; 10. a movable rod; 11. a locking device; 111. a U-shaped rod; 112. an internally threaded tube; 113. a screw; 114. a stopper; 115. a hand wheel; 12. a first fixed shaft; 13. a movable block; 14. a through hole; 15. a second fixed shaft; 16. a turn buckle; 17. a chute.

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.

As shown in fig. 1-4, the utility model provides a technical solution: a fatigue-resistant detection clamp for an aircraft engine blade comprises a fixed seat 1 and a sliding seat 2, wherein mounting holes are reserved at the corner positions of the fixed seat 1 and the sliding seat 2 and used for being mounted on detection equipment during use, a sliding block 3 is connected on the sliding seat 2 in a sliding manner, the sliding block 3 enables a chuck 4 to move left and right along the sliding seat 2, the turbine blade 6 is convenient to mount and take down and can also adapt to vibration along the axis direction of a turnbuckle 16, the chuck 4 is arranged on the sliding block 3 and the fixed seat 1, a through groove 5 is arranged at the bottom of the chuck 4, clamping grooves 7 which are matched with the turbine blade 6 in shape are arranged oppositely of the two chucks 4, clamping blocks 8 are arranged at the top and the bottom of the inner wall of each clamping groove 7, the clamping blocks 8 are also matched with the turbine blade 6 in shape, extrusion rods 9 are arranged on the deviating surfaces of the two clamping blocks 8 on the same vertical line, movable rods 10 are rotatably connected at the top of the top, the extrusion rod 9 penetrates through the chuck 4 and is movably sleeved on the surface of the movable rod 10, a locking device 11 is arranged between two movable rods 10 corresponding to the chuck 4, the locking device 11 and the turn buckle 16 are self-locked through threads, a first fixed shaft 12 is arranged on the front surface and the back surface of the inner wall of the through groove 5, the end portion of the first fixed shaft 12 is rotatably connected with a movable block 13, a through hole 14 is formed in the upper horizontal direction of the movable block 13, a second fixed shaft 15 is vertically arranged in the through hole 14, the turn buckle 16 is sleeved on the surface of the second fixed shaft 15, the movable block 13 is rotatably connected with the turn buckle 16 through the second fixed shaft 15, the first fixed shaft 12 and the second fixed shaft 15 are matched with the movable block 13 for use, the two ends of the turn buckle 16 can swing up and down and back and forth within a certain range, so that the vibration difference between the two.

As a technical optimization scheme of the utility model, be provided with on the slide 2 with the spout 17 of 3 shape looks adaptations of slider, the surface of slider 3 and the inner wall sliding connection of spout 17.

As a technical optimization scheme, the stripper 9 is including the stripper 91 that is located turbine fan blade 6 top and the stripper two 92 that is located turbine fan blade 6 below, the position department that the stripper 91 is close to the top is provided with perforation 93, the diameter of perforation 93 is accurate with upwards rotating movable rod 10 can drive a stripper 91 rebound segment distance, the diameter of perforation 93 can not be too little, the bottom of stripper two 92 is provided with draw-in groove 94, the surface at movable rod 10 is cup jointed through perforation 93 to stripper 91, stripper two 92 pass through the surface at movable rod 10 of draw-in groove 94 joint.

As a technical optimization scheme of the utility model, locking device 11 includes U-shaped pole 111, internal thread pipe 112, screw rod 113, dog 114 and hand wheel 115, and U-shaped pole 111 and internal thread pipe 112 are fixed connection respectively at the tip that corresponds two movable rods 10 of same chuck 4, and internal thread pipe 112 is located the top of U-shaped pole 111, screw rod 113 and internal thread pipe 112 threaded connection, dog 114 and hand wheel 115 are fixed connection respectively in the bottom and the top of screw rod 113.

When the device is used, the hand wheel 115 is rotated to drive the screw 113 to rotate and move downwards along the internal threaded pipe 112, the stop block 114 is separated from the U-shaped rod 111, at the moment, the hand wheel 115 can drive the first extrusion rod 91 to move upwards through the movable rod 10, the second extrusion rod 90 is not moved, so that the clamping blocks 8 above and below the turbine fan blades 6 can be separated, the turnbuckle 16 pushes the chucks 4 through the second fixed shaft 15, the movable block 13 and the first fixed shaft 12, so that one chuck 4 and the sliding block 3 move along the sliding groove 17, the distance between the two chucks 4 is increased, the turbine fan blades 6 can be taken out of or mounted in the clamping groove 7, then the turnbuckle 16 is rotated reversely, so that the two chucks 4 approach each other to clamp the turbine fan blades 6, then the hand wheel 115 is rotated reversely, so that the screw 113 moves upwards along the internal threaded pipe 112 to clamp the movable rod 10 through the stop block 114, the two movable rods 10, the turbine fan blades 6 are clamped through the clamping blocks 8, equipment vibrates during fatigue detection, and the two clamping heads 4 clamp the two ends of the turbine fan blades 6 respectively, so that the two ends of the turbine fan blades 6 are clamped tightly and are not easy to loosen, and detection is guaranteed to be smoothly carried out.

To sum up can, the utility model discloses a set up and press from both sides groove 7, grip block 8, fixed axle one 12, two 15, movable block 13 and turnbuckle 16, solved aircraft engine blade fatigue resistance testing in-process, to the independent centre gripping of blade one end, the blade other end causes the amplitude to be greater than the amplitude of anchor clamps one end by inertia, causes the not hard up problem of anchor clamps centre gripping easily.

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

Claims

1. The utility model provides an aircraft engine blade is able to bear or endure fatigue detection anchor clamps, includes fixing base (1) and slide (2), its characterized in that: the sliding seat is characterized in that a sliding block (3) is connected to the sliding seat (2) in a sliding mode, chucks (4) are arranged on the sliding block (3) and the fixing seat (1), a through groove (5) is formed in the bottom of each chuck (4), clamping grooves (7) matched with the shapes of the turbine fan blades (6) are formed in the two opposite sides of each chuck (4), clamping blocks (8) are arranged at the top and the bottom of the inner wall of each clamping groove (7), extrusion rods (9) are arranged on the back-off surfaces of the two clamping blocks (8) on the same vertical line, movable rods (10) are rotatably connected to the top of each chuck (4) and the top of the inner wall of each through groove (5), each extrusion rod (9) penetrates through each chuck (4) and is movably sleeved on the surface of each movable rod (10), a locking device (11) is arranged between the two corresponding movable rods (10) of each chuck (4), and fixed shafts (12) are arranged on the front and the back of the, the end part of the first fixed shaft (12) is rotatably connected with the movable block (13), a through hole (14) is formed in the movable block (13) in the horizontal direction, a second fixed shaft (15) is vertically arranged in the through hole (14), a turn buckle (16) is sleeved on the surface of the second fixed shaft (15), and the movable block (13) is rotatably connected with the turn buckle (16) through the second fixed shaft (15).

2. An aircraft engine blade fatigue resistance detection fixture as defined in claim 1, wherein: the sliding seat (2) is provided with a sliding groove (17) matched with the sliding block (3) in shape, and the surface of the sliding block (3) is connected with the inner wall of the sliding groove (17) in a sliding mode.

3. An aircraft engine blade fatigue resistance detection fixture as defined in claim 1, wherein: the utility model discloses a turbine fan blade, including turbine fan blade (6), the bottom of extrusion stem two (92) is provided with draw-in groove (94), the surface at movable rod (10) is cup jointed through perforation (93) in extrusion stem (9) including first (91) of the extrusion stem that is located turbine fan blade (6) top and the extrusion stem two (92) that is located turbine fan blade (6) below, the position department that extrusion stem one (91) is close to the top is provided with perforation (93), the bottom of extrusion stem two (92) is provided with draw-in groove (94), extrusion stem one (91) are through perforation (93), draw-in groove (94) joint is on the surface of.

4. An aircraft engine blade fatigue resistance detection fixture as defined in claim 1, wherein: locking device (11) are including U-shaped pole (111), internal thread pipe (112), screw rod (113), dog (114) and hand wheel (115), U-shaped pole (111) and internal thread pipe (112) are fixed connection respectively and are corresponding the tip of two movable rods (10) of same chuck (4), and internal thread pipe (112) are located the top of U-shaped pole (111), screw rod (113) and internal thread pipe (112) threaded connection, dog (114) and hand wheel (115) are fixed connection respectively at the bottom and the top of screw rod (113).