Aero-engine blade strength detection device

Abstract

The utility model discloses an aero-engine blade strength detection device, which comprises a fixed base, the fixed base is a plate with a cylindrical structure, a draw bar is arranged on the fixed base, the draw bar is in threaded connection with the fixed base, and a special-shaped butt clamp is arranged on the fixed base; the utility model relates to the technical field of aero-engine blade detection, in particular to an aero-engine blade strength detection device, which is characterized in that a hydraulic clamping fixture is designed aiming at the irregular end part of an aero-engine blade, and the hydraulic clamping fixture controls sliding blocks for fixing clamping blocks to move relatively through a linear screw rod module, so that a pair of clamping blocks correspond to two sides of the blade; the hydraulic follow-up clamping assembly is controlled through the hydraulic controller, the telescopic clamping rods arranged in a matrix mode on the follow-up clamping assembly clamp the blade, the structure is simple, flexible matching can be achieved according to the shape of the surface of the blade, and the effective fixing effect is achieved.

Description

TECHNICAL FIELD

[0001] The utility model relates to aviation vane detection technical field, concretely is aviation engine vane strength detection device. BACKGROUND

[0002] In the application process of modern aero-engine, in order to improve the running time of aero-engine and ensure the stable operation of aero-engine, the strength of the vane of aero-engine needs to be detected, to ensure that the aero-engine vane does not break, damage and other problems.

[0003] The present aero-engine vane strength detection is mainly divided into static strength detection, fatigue strength detection, vibration characteristic detection and high temperature performance detection and so on, and the vane needs to be fixed in each detection, and the present vane fixing often adopts the fixture setting, wherein the tail end of the engine is clamped by the fixture through the base of the vane, but the other end is not regular, so the fixture on the side needs to be customized, and the fixture cannot fully contact with the vane, so that the vane surface is easy to scratch or not fully fixed, in view of this, the above problems are deeply researched, and the case is generated. CONTENT OF THE UTILITY MODEL

[0004] In view of the deficiencies of the prior art, the utility model provides an aero-engine vane strength detection device, which solves the problems of the prior art.

[0005] To achieve the above purpose, the utility model realizes the following technical scheme: an aero-engine vane strength detection device, comprising a fixed base, the fixed base is a plate with a columnar structure, a traction rod is arranged on the fixed base, the traction rod is threadedly connected with the fixed base, and a special-shaped clamp is arranged on the fixed base.

[0006] The special-shaped clamp comprises a control motor, the control motor is installed on the fixed base, a pair of opposite adjusting grooves are arranged on the fixed base, a pair of sliding blocks are assembled in the adjusting grooves, a pair of hydraulic controllers are arranged on the sliding blocks, a pair of clamping plates are arranged on the opposite sides of the sliding blocks, and a pair of hydraulic follow-up clamping assemblies are arranged on the clamping plates.

[0007] The hydraulic follow-up clamping assemblies are connected with the hydraulic controllers.

[0008] A linear lead screw module is assembled between the adjusting grooves and connected with the sliding blocks, and the linear lead screw module is connected with the driving end of the control motor.

[0009] Preferably, the hydraulic follow-up clamping assembly comprises a flow distribution groove, the flow distribution groove is arranged between the clamping plate and the sliding block, a plurality of sliding holes are arranged on the clamping plate in a matrix, and a plurality of telescopic clamping rods are arranged in the plurality of sliding holes.

[0010] Preferably, the hydraulic controller comprises a hydraulic storage groove, and the hydraulic storage groove is provided with a control pump machine on one side.

[0011] Preferably, the control pump machine is provided with a flow distribution groove, and the flow distribution groove is communicated with the plurality of sliding holes through a plurality of tapered guide holes.

[0012] Preferably, the pair of adjusting grooves are a pair of rectangular structure grooves, and the pair of sliding blocks are matched with the width of the pair of adjusting grooves.

[0013] Preferably, the fixed base is movably connected with a fixed seat and a traction rod. Beneficial effects

[0014] The utility model provides a kind of aeroengine blade strength detection device.It has the following beneficial effects:The aeroengine blade strength detection device, irregular end of aeroengine blade is designed hydraulic clamping fixture, hydraulic clamping fixture controls the relative motion of the sliding block of fixed clamping block by linear lead screw module, so that a pair of clamping blocks correspond to the both sides of blade, and then by hydraulic controller controls hydraulic follow-up clamping assembly, so that a plurality of telescopic clamping rods arranged in matrix on follow-up clamping assembly are clamped to blade, not only simple structure, but also can be flexibly matched according to blade surface shape, effectively fixed. ACCURACY OF DRAWINGS

[0015] Fig. 1 It is the three-dimensional structure schematic diagram of the aeroengine blade strength detection device of the utility model.

[0016] Fig. 2 It is the partial sectional view structure schematic diagram of the aeroengine blade strength detection device of the utility model.

[0017] Fig. 3 It is the partial enlarged structure schematic diagram of the aeroengine blade strength detection device of the utility model.

[0018] In the drawing: 1, fixed base; 2, traction rod; 3, control motor; 4, adjusting groove; 5, sliding block; 6, clamping plate; 7, hydraulic follow-up clamping assembly; 8, hydraulic controller; 9, linear lead screw module; 71, flow distribution groove; 72, sliding hole; 73, telescopic clamping rod; 74, guide hole; 81, hydraulic storage groove; 82, communication pipeline; 83, control pump machine. DETAILED DESCRIPTION

[0019] The technical solutions in the embodiments of the utility model will be apparently and completely described in connection with the drawings in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, rather than all the embodiments. Based on the embodiments in the utility model, all the other embodiments obtained by the ordinary skilled in the art without creative labor belong to the protection scope of the utility model.

[0020] Please refer to Figs. 1-3 The utility model provides a kind of implementation scheme: in the process of modern aero-engine blade strength detection, blade needs to be fixed, however, the fixing device of present stage mainly relies on fixture fixed, however, the outer end of blade is mostly irregular shape, so the fixture of present stage is difficult to manufacture in clamping process, and there is small difference in blade production process, so single fixture cannot effectively match blade shape, and it is easy to cause scratch and damage to blade.

[0021] For the above problems, the application discloses an aero-engine blade strength detection device, including fixed base 1, fixed base 1 is the slab of column structure, fixed base 1 is arranged at one end of detection instrument, traction rod 2 is arranged on fixed base 1, traction rod 2 is connected with fixed base 1 by screw thread, traction rod 2 is connected with the test end of detection machine such as universal material testing machine, the control of detection force is realized by controlling the movement of traction rod 2, specifically, the special-shaped clamping device is arranged on fixed base 1, and the clamping action of engine blade is realized by special-shaped clamping device;

[0022] Specifically, according to the drawings in the specification Figs. 1-3 It can be known that the above-mentioned special-shaped clamping device includes control motor 3, control motor 3 is installed on fixed base 1, a pair of opposite adjusting through slots 4 are arranged on fixed base 1, a pair of sliding blocks 5 are assembled in a pair of adjusting through slots 4, a pair of hydraulic controllers 8 are arranged on a pair of sliding blocks 5, a pair of clamping plates 6 are arranged on the opposite side of a pair of sliding blocks 5, and a pair of hydraulic follow-up clamping assemblies 7 are arranged on a pair of clamping plates 6.

[0023] In the specific implementation process, the pair of sliding blocks 5 can be limited and guided through the pair of adjusting through grooves 4 on the fixed base 1, a linear lead screw module 9 is assembled between the pair of adjusting through grooves 4 and connected with the pair of sliding blocks 5, and the linear lead screw module 9 is connected with the driving end of the control motor 3; the linear relative movement of the pair of sliding blocks 5 in the pair of adjusting through grooves 4 can be adjusted through the linear lead screw module 9; a pair of clamping plates 6 are arranged on the pair of sliding blocks 5; and the two sides of the irregular blade surface are clamped through the pair of hydraulic follow-up clamping assemblies 7 on the pair of clamping plates 6; the pair of hydraulic follow-up clamping assemblies 7 are connected with a pair of hydraulic controllers 8; the movement of the pair of hydraulic follow-up clamping assemblies 7 is controlled through the pair of hydraulic controllers 8; the hydraulic oil is stored in the pair of hydraulic controllers 8; the hydraulic oil is pumped into the hydraulic follow-up clamping assemblies 7 through the hydraulic controller 8; and the clamping of the aero-engine blade is completed by using the follow-up action of the follow-up clamping assembly.

[0024] As a preferred solution, further, according to the description attached Figs. 1-3 It can be known that the hydraulic follow-up clamping assembly 7 comprises a shunt groove 71, the shunt groove 71 is arranged between the clamping plate 6 and the sliding block 5, a plurality of sliding holes 72 are arranged on the clamping plate 6 in a matrix, a plurality of telescopic clamping rods 73 are assembled in the plurality of sliding holes 72, the plurality of telescopic clamping rods 73 are communicated with the plurality of sliding holes 72, the shunt groove 71 is connected with the hydraulic controller 8, the hydraulic oil in the hydraulic controller 8 is controlled to enter the clamping plate 6, the hydraulic oil is shunted by using the shunt groove 71 in the clamping plate 6, the plurality of telescopic clamping rods 73 are moved in and out of the plurality of sliding holes 72, so that the telescopic clamping rods 73 matched clamp different surfaces of the blade, and the head end fixing action of the blade is realized.

[0025] As a preferred solution, further, according to the description attached Figs. 1-3 It can be known that the hydraulic controller 8 comprises a hydraulic storage groove 81, a communication pipeline 82 is arranged on one side of a control pump 83 and communicated with the shunt groove 71, and the control pump 83 is arranged on one side of the hydraulic storage groove 81.

[0026] In the specific implementation process, the hydraulic oil is pumped out of the hydraulic storage groove 81 by the control pump 83, so that the hydraulic oil is delivered to the shunt groove 71 through the communication pipeline 82, the hydraulic pressure in the shunt groove 71 is controlled by using the valve on the communication pipeline 82, the plurality of telescopic clamping rods 73 are prevented from sliding back and other problems by the pressure action of the hydraulic oil, the clamping force of the blade is maintained, and the hydraulic oil in the shunt groove 71 is extracted in the reverse direction by the control pump 83 to unload the pressure when the detection is completed.

[0027] As a preferred solution, further, the control pump 83 is provided with the shunt groove 71, the shunt groove 71 is communicated with the plurality of sliding holes 72 through a plurality of tapered structure flow guide holes 74, and the effect of guiding the hydraulic oil is achieved.

[0028] As a preferred solution, further, the pair of adjusting grooves 4 are a pair of rectangular structure grooves, and the pair of sliding blocks 5 are matched with the width of the pair of adjusting grooves 4.

[0029] As a preferred solution, further, the fixed base 1 is movably connected with a fixed seat connected with the traction rod 2, and the fixed base 1 and the fixed seat are coaxially movably connected, so that the fixed base 1 can be at different angles according to the torsion angle of the blade.

[0030] In summary, the aviation engine blade strength detection device, the irregular end of the aviation engine blade is designed with a hydraulic clamping fixture, the hydraulic clamping fixture controls the relative movement of the sliding block 5 of the fixed clamping block through the linear lead screw module 9, so that a pair of clamping blocks correspond to the two sides of the blade, and then the hydraulic controller 8 controls the hydraulic follow-up clamping assembly 7, so that a plurality of telescopic clamping rods 73 arranged in a matrix on the follow-up clamping assembly clamp the blade, which not only has a simple structure, but also can be flexibly matched according to the shape of the blade surface, and effectively fixed.

[0031] Although the embodiments of the utility model have been shown and described, it can be understood by those skilled in the art that various changes, modifications, replacements and variations can be made to these embodiments without departing from the principles and spirits of the utility model, and the scope of the utility model is defined by the appended claims and their equivalents.

Claims

1. An aero-engine blade strength detection device, comprising a fixed base (1), the fixed base (1) is a plate with a columnar structure, a traction rod (2) is arranged on the fixed base (1), and the traction rod (2) is in threaded connection with the fixed base (1), characterized in that, The fixing base (1) is provided with a special-shaped clamping device; The special-shaped clamping device comprises a control motor (3) installed on the fixing base (1), the fixing base (1) is provided with a pair of opposite adjusting through grooves (4), a pair of sliding blocks (5) are assembled in the adjusting through grooves (4), a pair of hydraulic controllers (8) are arranged on the sliding blocks (5), a pair of clamping plates (6) are arranged on the opposite sides of the sliding blocks (5), and a pair of hydraulic follow-up clamping assemblies (7) are arranged on the clamping plates (6). The hydraulic follow-up clamping assemblies (7) are connected with the hydraulic controllers (8). A linear lead screw module (9) is assembled between the adjusting through grooves (4) and connected with the sliding blocks (5), and the linear lead screw module (9) is connected with the driving end of the control motor (3).

2. The aircraft engine blade strength detection device of claim 1, wherein, The hydraulic follow-up clamping assembly (7) comprises a shunt groove (71), the shunt groove (71) is arranged between the clamping plate (6) and the sliding block (5), a plurality of sliding holes (72) are arranged on the clamping plate (6) in a matrix arrangement, a plurality of telescopic clamping rods (73) are assembled in the sliding holes (72), and the telescopic clamping rods (73) are communicated with the sliding holes (72).

3. The apparatus of claim 2, wherein, The hydraulic controller (8) comprises a hydraulic storage groove (81), one side of the hydraulic storage groove (81) is provided with a control pump (83), one side of the control pump (83) is provided with a communication pipeline (82) communicated into the shunt groove (71).

4. The apparatus of claim 3, wherein, The control pump (83) is provided with a shunt groove (71), and the shunt groove (71) and the plurality of sliding holes (72) are communicated through a plurality of tapered structure flow guide holes (74).

5. The apparatus of claim 4, wherein, The adjusting through grooves (4) are a pair of rectangular structure grooves, the sliding blocks (5) are matched with the width of the adjusting through grooves (4).

6. The apparatus of claim 5, wherein, The fixing base (1) is movably connected with the fixing seat connected with the traction rod (2).

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