Aero-engine blade clamping mechanism

Abstract

The invention relates to an aero-engine blade clamping mechanism which is characterized in that a fixed seat is fixedly mounted on a diffractometer, a sliding table is movably mounted on the fixed seat in the first direction, a rotating frame is rotatably mounted on the sliding table in the second direction, and a clamping assembly used for clamping a blade is rotatably mounted on the rotating frame in the third direction; two clamping jaws, located at different heights, of the clamping assembly are installed on two piston rods correspondingly and are pushed by the piston rods to be opened and closed, and clamping columns are rotatably installed on the clamping jaws and work cooperatively with the clamping jaws so as to be embedded into groove parts of tenons of the blades to achieve clamping. According to the aero-engine blade clamping mechanism, the horizontal fixing base is fixed to a diffractometer, irregular blade tenons can be clamped through the clamping columns, blades of different models can be clamped through the air cylinder, reliable positioning is ensured, three-degree-of-freedom movement of the blades is achieved, the blades are adjusted through three degrees of freedom to be compatible with the diffractometer, and the blade clamping mechanism is suitable for the diffractometer. And X-ray nondestructive testing is realized.

Description

Technical Field

[0001] The invention relates to X-ray nondestructive testing, and more particularly to an aero-engine blade clamping mechanism. Background Art

[0002] Aircraft engine blades are key components of aircraft engines. As the heart of an aircraft, the engine is known as the "flower of industry". It directly affects the performance and reliability of an aircraft. The inspection of engine blades is an important inspection work related to aircraft safety and has important significance for national defense and the national economy.

[0003] Conventional engine blade inspection methods, such as the indentation method, are destructive inspection methods. X-ray diffraction and CT are non-destructive inspection methods that can obtain early warning information when changes have occurred inside the blade but changes are not visible on the surface.

[0004] Since blades are special-shaped parts, known aircraft engine blade fixtures generally have the problem of unreliable positioning when clamping blades of different models. In addition, there are certain limitations on the horizontal movement, horizontal rotation, left and right swing of the blades during the test, and the scope of application, making it difficult to be compatible with the use requirements of the diffractometer. Summary of the invention

[0005] In order to overcome the limitations of the known aircraft engine blade clamps in the prior art, the present invention provides an aircraft engine blade clamping mechanism.

[0006] According to the aircraft engine blade clamping mechanism of the present invention, it includes a fixed seat, a sliding table, a rotating frame and a clamping assembly, wherein the fixed seat is fixedly mounted on the diffractometer, the sliding table is movably mounted on the fixed seat along a first direction, the rotating frame is rotatably mounted on the sliding table along a second direction, and the clamping assembly for clamping the blade is rotatably mounted on the rotating frame along a third direction. The clamping assembly includes a cylinder, a clamping jaw and a clamping column. The cylinder includes a main body and two piston rods. The main body is rotatably mounted on the rotating frame. Two clamping jaws located at different heights are respectively mounted on two piston rods and open and close under the push of the piston rods. The clamping column is rotatably mounted on the clamping jaw and works in conjunction with the clamping jaw to embed into the groove portion of the tenon of the blade to achieve clamping.

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

[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 fixing seat has opposite longitudinally extending strip grooves, and the two sides of the sliding platform are accommodated in the strip grooves to slide freely, thereby realizing horizontal movement of the blades.

[0010] In a preferred embodiment, one end of the sliding table adjacent to the rotating frame has a sliding table rotation hole, and one end of the rotating frame adjacent to the sliding table has a rotating frame rotation hole. Both ends of the longitudinally extending rotating pin are respectively inserted into the sliding table rotation hole and the rotating frame rotation hole for installation, 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 to achieve 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, two central cylinders of each clamping column are embedded in the groove of the tenon to clamp the blade.

[0014] In a preferred embodiment, a fixing seat threaded hole is provided on the side end surface of the fixing seat, and a transversely extending locking pin is inserted into the fixing seat threaded hole for installation, so that the sliding platform is pressed against the fixing seat.

[0015] In a preferred embodiment, a positioning pin hole for connecting the fixing base of the diffractometer is provided at the bottom end of the fixing base.

[0016] The aircraft engine blade clamping mechanism according to the present invention is fixed to the diffractometer through a horizontal fixing seat, irregular blade tenons can be clamped through clamping columns, different types of blades can be clamped by cylinders and reliable positioning can be ensured, three-degree-of-freedom movement of the blades can be achieved, and the three degrees of freedom are used to adjust the blades to be compatible with the diffractometer, thereby achieving X-ray nondestructive testing, including reflection and grazing incidence experiments, and the operation is simple. BRIEF DESCRIPTION OF THE DRAWINGS

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

[0018] Figure 2 The blade is shown clamped in Figure 1 Aircraft engine blade clamping mechanism.

[0019] Figure 3 yes Figure 2 Side view of.

[0020] Figure 4 yes Figure 2 Top view of the .

[0021] Figure 5 yes Figure 1 Schematic diagram of the structure of the clamping assembly. DETAILED DESCRIPTION

[0022] The present invention is described in detail below in conjunction with the accompanying drawings and examples. The following examples are used to further illustrate the present invention, but should not be construed as fixing or limiting the present invention. If not specifically indicated, the technical features used in the examples can be replaced by other technical features known in the art that have equivalent or similar functions or effects without departing from the inventive concept.

[0023] like Figure 1 As shown, the aircraft engine blade clamping mechanism according to a preferred embodiment of the present invention comprises a fixed seat 1, a sliding table 2, a rotating frame 3 and a clamping assembly A, wherein the fixed seat 1 is fixedly mounted on a diffractometer (not shown), the sliding table 2 is movably mounted on the fixed seat 1 along a first direction 8, and the rotating frame 3 is rotatably mounted on the sliding table 2 along a second direction 9 for clamping the blade 7 (see Figure 2-Figure 4 ) is rotatably mounted on the rotating frame 3 along a third direction 10.

[0024] In this way, when the sliding table 2 moves along the first direction 8 relative to the fixed seat 1, the clamping assembly A linked to the driving sliding table 2 drives the blade 7 to achieve the first degree of freedom of translation; when the rotating frame 3 rotates along the second direction 9 relative to the sliding table 2, the clamping assembly A linked to the rotating frame 3 drives the blade 7 to achieve the second degree of freedom of rotation; when the clamping assembly A rotates along the third direction 10 relative to the rotating frame 3, the clamping assembly A drives the blade 7 to achieve the third degree of freedom of rotation. In this embodiment, the fixed seat 1 is a horizontal fixed seat, 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 short, the aircraft engine blade clamping mechanism according to the present invention has three degrees of freedom, which can realize the functions of horizontal movement, horizontal rotation and left-right rotation of the blade 7.

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

[0026] like Figure 1 As shown, one end of the sliding table 2 adjacent to the rotating frame 3 has a sliding table rotating hole, and one end of the rotating frame 3 adjacent to the sliding table 2 has a rotating frame rotating hole. Both ends of the 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 the horizontal axis to realize the blade 7 (see Figure 2-Figure 4 ) radial rotation.

[0027] like Figure 1 As shown, 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 blade 7 (see Figure 2-Figure 4 ) axial rotation.

[0028] like Figure 5 As shown, the clamping assembly A includes a cylinder 4, a clamping jaw 5 and a clamping column 6, wherein the cylinder 4 is the power source of the clamping assembly A and includes a body and two piston rods, and the body is horizontally (see Figure 1 ) is rotatably mounted in the groove of the rotating frame 3, two clamping jaws 5 located at different heights are respectively mounted on two piston rods, and a clamping column 6 is rotatably mounted on the clamping jaws 5 to act on the blade 7 (see Figure 2-Figure 4 ). In this way, the clamping jaw 5 is opened and closed under the push of the piston rod of the 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 clamp column 6 is a triangular clamp column composed of three cylinders. Since the tenon of the blade 7 is groove-shaped but has an irregular contour, the triangular clamp column is fixed in a point / line manner, so that the irregular tenon of the blade 7 is firmly clamped by the clamp column 6. When the cylinder 4 drives the clamping jaws 5 to approach the tenon of the blade 7 to clamp, the clamp column 6 rotates freely, so that the four cylinders (two each at the top and bottom) in the middle are embedded in the groove of the tenon. Although they cannot be completely in contact, there are at least four points of contact, which improves the adaptability of the aircraft engine blade clamping mechanism. In addition, since the cylinder 4 can provide sufficient holding force, for example, a clamping force of nearly 50N under a pressure of 0.5MPa, stable clamping of the blade 7 can be achieved.

[0030] It should be understood that the specific structures 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 their travel range can be increased according to actual needs. For example, the motion range of the adapter device that can be accepted by diffraction is (-10, +10), and the mechanical design of the corresponding motion range can be installed, which is flexible and adjustable.

[0031] The above is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. The above embodiment of the present invention can also be modified in various ways. That is, all simple, equivalent changes and modifications made according to the claims and the contents of the specification of the present invention fall within the scope of protection of the claims of the present invention. Anything not described in detail in the present invention is within the conventional technology.

Claims

1. An aircraft engine blade clamping mechanism, characterized in that: The aircraft engine blade clamping mechanism comprises a fixed seat, a sliding table, a rotating frame and a clamping assembly, wherein the fixed seat is fixedly mounted on the diffractometer, the sliding table is movably mounted on the fixed seat along a first direction, the rotating frame is rotatably mounted on the sliding table along a second direction, and the clamping assembly for clamping the blade is rotatably mounted 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 main body and two piston rods. The main body is rotatably mounted on the rotating frame. Two clamping jaws located at different heights are respectively mounted on two piston rods and open and close under the push of the piston rods. The clamping column is rotatably mounted on the clamping jaw and cooperates with the clamping jaw to embed into the groove of the tenon of the blade to achieve clamping.

2. The aircraft engine blade clamping mechanism according to claim 1, characterized in that: When the sliding table moves along a first direction relative to the fixed seat, the clamping assembly linked to the sliding table drives the blade to achieve a first degree of freedom of translation; when the rotating frame rotates along a second direction relative to the sliding table, the clamping assembly linked to the rotating frame drives the blade to achieve a second degree of freedom of rotation; when the clamping assembly rotates along a third direction relative to the rotating frame, the clamping assembly drives the blade to achieve a third degree of freedom of rotation.

3. The aircraft engine blade clamping mechanism according to claim 2, characterized in that: 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.

4. The aircraft engine blade clamping mechanism according to claim 3, characterized in that: The fixing seat has opposite longitudinally extending strip grooves, and the two sides of the sliding platform are accommodated in the strip grooves to slide freely, so as to realize the horizontal movement of the blades.

5. The aircraft engine blade clamping mechanism according to claim 3, characterized in that: One end of the sliding table adjacent to the rotating frame has a sliding table rotating hole, and one end of the rotating frame adjacent to the sliding table has a rotating frame rotating hole. Both ends of the longitudinally extending rotating pin are respectively inserted into the sliding table rotating hole and the rotating frame rotating hole for installation to achieve radial rotation of the blade.

6. The aircraft engine blade clamping mechanism according to claim 3, characterized in that: The rotating frame has a groove, and the clamping assembly is rotatably installed in the groove through a transversely extending rotating shaft to realize the axial rotation of the blade.

7. The aircraft engine blade clamping mechanism according to claim 1, characterized in that: Each clamping column is a triangular clamping column composed of three cylinders.

8. The aircraft engine blade clamping mechanism according to claim 7, characterized in that: The two central cylinders of each clamping column are embedded in the groove of the tenon to clamp the blade.

9. The aircraft engine blade clamping mechanism according to claim 1, characterized in that: A fixing seat threaded hole is arranged on the side end surface of the fixing seat, and a transversely extending locking pin is inserted into the fixing seat threaded hole for installation, so that the sliding platform is pressed against the fixing seat.

10. The aircraft engine blade clamping mechanism according to claim 1, characterized in that: The bottom end of the fixing seat is provided with a positioning pin hole for connecting the fixing seat of the diffractometer.

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