An aeroengine blade clamping mechanism

Abstract

The present application relates to a kind of aero-engine blade clamping mechanism, fixed seat is fixedly installed on diffractometer, sliding table is movably installed on fixed seat along first direction, rotating frame is rotatably installed on sliding table along second direction, clamping assembly for clamping blade is rotatably installed on rotating frame along third direction, two clamping jaws of clamping assembly at different heights are respectively installed on two piston rods and open-close action is carried out under the push of piston rod, clamping column is rotatably installed on clamping jaw and cooperates with clamping jaw to embed in the groove of tenon of blade to realize clamping.According to the aero-engine blade clamping mechanism of the present application, the diffractometer is fixed by horizontal fixed seat, the irregular tenon of blade can be clamped by clamping column, different models of blade can be clamped and positioning is reliable by air cylinder, three degrees of freedom motion of blade is realized, three degrees of freedom are used to adjust blade to be compatible with diffractometer, and X-ray nondestructive testing is realized.

Description

TECHNICAL FIELD

[0001] The present application relates to X-ray nondestructive testing, and more particularly to an aero-engine blade clamping mechanism. BACKGROUND

[0002] Aero-engine blade is a key component of aircraft engine, and the engine, as the heart of the aircraft, is known as the "industrial flower", which directly affects the performance and reliability of the aircraft. The detection of the engine blade is an important detection work related to the safety of the aircraft, and has important significance to national defense and national economy.

[0003] The conventional engine blade detection method, such as indentation method, is a destructive detection method. The X-ray based diffraction and CT are nondestructive detection methods, which can obtain early warning information when the internal changes of the blade have occurred, although the changes on the surface of the blade cannot be seen.

[0004] Since the blade is a special-shaped part, the known aero-engine blade clamp generally has the problem of unreliable positioning when clamping different types of blades, and has certain limitations for the horizontal movement, horizontal rotation, left and right swing of the blade during testing, and the application range, etc., and it is difficult to meet the use requirements of the diffractometer. SUMMARY

[0005] In order to overcome the limitations of the known aero-engine blade clamp in the prior art, the present application provides an aero-engine blade clamping mechanism.

[0006] The aero-engine blade clamping mechanism according to the present application comprises a fixed seat, a sliding table, a rotating frame and a clamping assembly, wherein the fixed seat is fixedly installed on a diffractometer, the sliding table is movably installed on the fixed seat along a first direction, the rotating frame is rotatably installed on the sliding table along a second direction, and the clamping assembly for clamping the blade is rotatably installed on the rotating frame along a third direction. The clamping assembly comprises a cylinder, a clamping jaw and a clamping column. The cylinder comprises a body and two piston rods. The body is rotatably installed on the rotating frame. The two clamping jaws at different heights are respectively installed on the two piston rods and perform opening and closing actions under the pushing of the piston rods. The clamping column is rotatably installed on the clamping jaw and cooperates with the clamping jaw to embed into the groove of the tenon of the blade to achieve clamping.

[0007] In the preferred embodiment, when the sliding table moves relative to the fixed seat along the first direction, the clamping assembly linked with the sliding table drives the blade to realize the translation of the first degree of freedom; when the rotating frame rotates relative to the sliding table along the second direction, the clamping assembly linked with the rotating frame drives the blade to realize the rotation of the second degree of freedom; when the clamping assembly rotates relative to the rotating frame along the third direction, the clamping assembly drives the blade to realize the rotation of the third degree of freedom.

[0008] In a preferred embodiment, the first degree of freedom is a horizontal displacement degree of freedom, the second degree of freedom is a radial rotation degree of freedom, and the third degree of freedom is an axial rotation degree of freedom.

[0009] In a preferred embodiment, the fixed seat has opposite longitudinally extending strip-shaped grooves, and the two sides of the sliding table are accommodated in the strip-shaped grooves to freely slide, thereby realizing horizontal movement of the blade.

[0010] In a preferred embodiment, one end of the sliding table adjacent to the rotating frame has a sliding table rotating hole, one end of the rotating frame adjacent to the sliding table has a rotating frame rotating hole, and two ends of a longitudinally extending rotating pin are respectively inserted into the sliding table rotating hole and the rotating frame rotating hole to be installed, thereby realizing radial rotation of the blade.

[0011] In a preferred embodiment, the rotating frame has a groove, and the clamping assembly is rotatably installed in the groove through a transversely extending rotating shaft, thereby realizing axial rotation of the blade.

[0012] In a preferred embodiment, each clamping column is a triangular clamping column composed of three cylinders.

[0013] In a preferred embodiment, the two cylinders in the middle of each clamping column are embedded in the groove part of the tenon to clamp the blade.

[0014] In a preferred embodiment, the side end surface of the fixed seat is provided with a fixed seat threaded hole, and a transversely extending locking pin is inserted into the fixed seat threaded hole to be installed, so that the sliding table is pressed against the fixed seat.

[0015] In a preferred embodiment, the bottom end of the fixed seat is provided with a fixed seat positioning pin hole for connecting the diffractometer.

[0016] According to the aircraft engine blade clamping mechanism of the present application, the blade can be clamped and reliably positioned for different models by the cylinder, three degrees of freedom are used to adjust the blade to be compatible with the diffractometer, X-ray nondestructive testing is realized, including reflection and grazing incidence experiments, and the operation is simple. BRIEF DESCRIPTION OF DRAWINGS

[0017] Figure 1 is a schematic diagram of the overall structure of the aircraft engine blade clamping mechanism according to a preferred embodiment of the present application.

[0018] Figure 2 shows that the blade is clamped in Figure 1 the aircraft engine blade clamping mechanism.

[0019] Figure 3 is a side view of Figure 2 .

[0020] Figure 4 is Figure 2 a top view.

[0021] Figure 5 is Figure 1 a structural schematic diagram of the clamping assembly. DETAILED DESCRIPTION

[0022] The application will be described in detail below with reference to the drawings and embodiments. The following embodiments are used to further illustrate the application, but should not be understood as a fixed or limited application. If not specifically indicated, the technical features used in the embodiments can be replaced by other known technical features in the art with equivalent or similar functions or effects without departing from the concept of the application.

[0023] As shown in Figure 1 , the aero-engine blade clamping mechanism according to one preferred embodiment of the application comprises a fixed base 1, a sliding table 2, a rotating frame 3 and a clamping assembly A, wherein the fixed base 1 is fixedly installed on a diffractometer (not shown in the figure), the sliding table 2 is movably installed on the fixed base 1 along a first direction 8, the rotating frame 3 is rotatably installed on the sliding table 2 along a second direction 9, and the clamping assembly A for clamping a blade 7 (see Figures 2-4 ) is rotatably installed on the rotating frame 3 along a third direction 10.

[0024] Thus, when the sliding table 2 moves relative to the fixed base 1 along the first direction 8, the clamping assembly A linked with the driving of the sliding table 2 drives the blade 7 to realize the translation of the first degree of freedom; when the rotating frame 3 rotates relative to the sliding table 2 along the second direction 9, the clamping assembly A linked with the rotating frame 3 drives the blade 7 to realize the rotation of the second degree of freedom; when the clamping assembly A rotates relative to the rotating frame 3 along the third direction 10, the clamping assembly A drives the blade 7 to realize the rotation of the third degree of freedom. In this embodiment, the fixed base 1 is a horizontal fixed base, the sliding table 2 is a horizontal sliding table, the first degree of freedom is the horizontal displacement degree of freedom, the second degree of freedom is the radial rotation degree of freedom, and the third degree of freedom is the axial rotation degree of freedom. In summary, the aero-engine blade clamping mechanism according to the application has three degrees of freedom, which can realize the functions of horizontal movement, horizontal rotation and left-right rotation of the blade 7.

[0025] As shown in Figure 1 , the fixed base 1 has opposite longitudinally extending strip-shaped grooves 11, and the two sides of the sliding table 2 are accommodated in the strip-shaped grooves 11 to freely slide, so that the sliding table 2 is clamped on the fixed base 1 to slide horizontally, realizing the horizontal movement of the blade 7 (see Figures 2-4The side end face of the fixed base 1 is provided with a fixed base threaded hole, and a transversely extending locking pin 12 is inserted into the fixed base threaded hole for installation, so that the sliding table 2 can be pressed against the fixed base 1 after sliding to the desired position. The bottom end of the fixed base 1 is provided with a positioning pin hole (not shown in the figure) for connecting the fixed base of the diffractometer to realize X-ray nondestructive testing.

[0026] As shown in Figure 1 , one end of the sliding table 2 adjacent to the rotating frame 3 is provided with a sliding table rotating hole, and one end of the rotating frame 3 adjacent to the sliding table 2 is provided with a rotating frame rotating hole, and two ends of a longitudinally extending rotating pin are respectively inserted into the sliding table rotating hole and the rotating frame rotating hole for installation, so that the rotating frame 3 can rotate around a horizontal axis to realize the radial rotation of the blade 7 (see Figures 2-4 ).

[0027] As shown in Figure 1 , the rotating frame 3 has a groove, and the clamping assembly A is rotatably installed in the groove through a transversely extending rotating shaft to realize the axial rotation of the blade 7 (see Figures 2-4 ).

[0028] As shown in Figure 5 , the clamping assembly A includes a gas cylinder 4, a clamping jaw 5 and a clamping column 6, wherein the gas cylinder 4 is the power source of the clamping assembly A and includes a body and two piston rods, the body is rotatably installed in the groove of the rotating frame 3 through a transversely (see Figure 1 ) extending rotating shaft, the two clamping jaws 5 at different heights are respectively installed on the two piston rods, and the clamping column 6 is rotatably installed on the clamping jaw 5 to act on the blade 7 (see Figures 2-4 ). In this way, the clamping jaw 5 opens and closes under the push of the piston rod of the gas cylinder 4, and the clamping column 6 cooperates with the clamping jaw 5 to enhance the clamping force and provide additional stability.

[0029] In this embodiment, the clamping column 6 is a triangular clamping column composed of three cylinders. Since the tenon of the blade 7 is of a groove type but has an irregular profile, the triangular clamping column adopts a point / line mode for fixation, so as to firmly clamp the irregular tenon of the blade 7 through the clamping column 6. When the gas cylinder 4 drives the clamping jaws 5 to approach each other to clamp the tenon of the blade 7, the clamping column 6 rotates freely, so that the four (two above and two below) middle cylinders are embedded in the groove part of the tenon, although they cannot completely contact, but at least four points contact, improving the adaptability of the aero-engine blade clamping mechanism. Moreover, since the gas cylinder 4 can provide sufficient clamping force, for example, nearly 50N clamping force under 0.5MPa gas pressure, stable clamping of the blade 7 can be realized.

[0030] It should be understood that the specific structure of the fixed seat 1, the sliding table 2, the rotating frame 3 and the clamping assembly A can be mechanically designed as needed, and the travel thereof can be increased according to actual needs, for example, the motion range of the adapter device acceptable to diffraction is (-10, +10), and a mechanical design with a corresponding motion range can be installed for flexible adjustment.

[0031] The above description is only a preferred embodiment of the present application, and is not intended to limit the scope of the present application. The above-described embodiments of the present application can be variously changed. That is, simple, equivalent changes and modifications made in accordance with the content of the claims and the specification of the present application are within the scope of the present application. The present application is not described in detail, and is within the scope of conventional technology.

Claims

1. An aero-engine blade clamping mechanism, characterized in that, The aero-engine blade clamping mechanism includes a fixed base, a sliding stage, a rotating frame, and a clamping assembly. The fixed base is fixedly mounted on the diffractometer. The sliding stage is movably mounted on the fixed base along a first direction. The rotating frame is rotatably mounted on the sliding stage along a second direction. The clamping assembly for clamping the blades is rotatably mounted on the rotating frame along a third direction. The clamping assembly includes a cylinder, grippers, and clamping pins. The cylinder includes a body and two piston rods. The body is rotatably mounted on the rotating frame. Two grippers located at different heights are respectively mounted on the two piston rods and open and close under the push of the piston rods. The clamping pins are rotatably mounted on the grippers and work in conjunction with the grippers. Each gripper... The column is a triangular clamping column composed of three cylinders. The two middle cylinders of each clamping column are embedded in the grooves of the tenon of the blade to clamp the blade. When the sliding table moves relative to the fixed seat along the first direction, the clamping assembly linked to the sliding table drives the blade to achieve the first degree of freedom of translation. When the rotating frame rotates relative to the sliding table along the second direction, the clamping assembly linked to the rotating frame drives the blade to achieve the second degree of freedom of rotation. When the clamping assembly rotates relative to the rotating frame along the third direction, the clamping assembly drives the blade to achieve the third degree of freedom of rotation. The first degree of freedom is the horizontal displacement degree of freedom, the second degree of freedom is the radial rotational degree of freedom, and the third degree of freedom is the axial rotational degree of freedom.

2. The aero-engine blade clamping mechanism according to claim 1, characterized in that, The fixed base has relatively longitudinally extending strip grooves, and the two sides of the sliding table are accommodated in the strip grooves and slide freely to realize the horizontal movement of the blade.

3. The aero-engine blade clamping mechanism according to claim 1, characterized in that, The sliding table has a sliding table rotation hole at one end adjacent to the rotating frame, and the rotating frame has a rotating frame rotation hole at one end adjacent to the sliding table. The two ends of the longitudinally extending rotating pin are respectively inserted into the sliding table rotation hole and the rotating frame rotation hole to achieve radial rotation of the blade.

4. The aero-engine blade clamping mechanism according to claim 1, characterized in that, The rotating frame has a groove in which the clamping assembly is rotatably mounted via a laterally extending rotating shaft, enabling axial rotation of the blade.

5. The aero-engine blade clamping mechanism according to claim 1, characterized in that, The side end face of the fixed seat is provided with a fixed seat threaded hole, and the laterally extending locking pin is inserted into the fixed seat threaded hole for installation, so that the sliding table is pressed against the fixed seat.

6. The aero-engine blade clamping mechanism according to claim 1, characterized in that, The bottom of the mounting base is provided with a positioning pin hole for connecting the mounting base of the diffractometer.

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