Universal aero-engine blade test clamping device and method

Abstract

The invention provides a general aero-engine blade test clamping device and method, the general aero-engine blade test clamping device comprises a gantry, a gland, a top block and a clamp body, the side surface of the lower part of the gantry is provided with a gantry fixing groove, and the upper part of the gantry is provided with a gantry screw hole; one end of the clamp body is provided with a dovetail groove structure; the ejector block is arranged in a clamp body screw hole in the clamp body, and the gland is pressed on the upper portion of the clamp body. The clamping method comprises the following steps of: fixing the gantry tool: fixing the gantry on the vibration table surface of the vibration table by using a standard bolt through a fixing groove of the gantry, and ensuring the maximum rigid connection. Mounting a clamp body; the clamp body is fixed. And mounting the blades. The method has the advantages that test requirements are met, vibration test quality is guaranteed, scientific research test verification is completed, and an expected effect is achieved. The vibration test period of the related blade is greatly shortened, and the test cost is reduced. And meanwhile, the design thought of the vibration test compressor blade clamping device is expanded.

Description

Technical Field

[0001] The invention relates to the field of aero-engine blade testing, and in particular to a universal aero-engine blade testing clamping device and method. Background Art

[0002] The clamping devices used in the existing vibration test of aircraft engine blades usually require different clamping devices for blades of different levels. This is because there is a torsion angle between the tenon and the blade body of the aircraft engine compressor blade. The torsion angles of blades of different levels of the same model compressor are different. Therefore, when testing the natural frequency of the blade, in order to keep the blade body horizontal, the blade tenon dovetail groove part of the clamping device used is at an angle to the horizontal. There are about 9 levels of aircraft engine compressor blades. If a special clamping device is made for each level of blades of each model engine, a large number of blade tenon clamping devices with high dimensional accuracy need to be processed, which is time-consuming, labor-intensive and costly.

[0003] The clamping device used in the traditional compressor blade vibration test is fixed to the vibration table surface with standard bolts through the fixing groove of the clamping device to ensure the maximum rigid connection. The top block is inserted from the screw hole at the back of the clamping device, and then ejected from the top block outlet through the bolt. When testing the blade, the blade is slid into the dovetail groove of the clamping device at one end, aligned with the top block outlet position, and the blade is clamped with a force-limiting wrench. Generally, there is an angle between the blade body and the installation tenon of the compressor blade. Therefore, when performing the blade vibration test, in order to ensure the horizontal clamping of the blade body, the dovetail groove and the horizontal plane must have a matching angle. In many cases, the tenon sizes of the first few stages of the compressor blades are the same, but the angles between the blade body and the tenon are different. However, in order to ensure the accuracy of the blade vibration test, a set of professional clamping devices must be used for each level of blade. Summary of the invention

[0004] The purpose of the present invention is to solve the problem that a blade can only be clamped by a dedicated set of clamping devices. The blade tenon clamping groove can be rotated at any angle, and the blade body can be clamped horizontally as much as possible. A universal aircraft engine blade test clamping device and method are specially provided.

[0005] The present invention provides a universal aircraft engine blade test clamping device and method, which is characterized by:

[0006] The universal aircraft engine blade test clamping device comprises a gantry 1, a pressure cover 5, a top block 3, and a clamp body 6. The lower side of the gantry 1 is provided with a gantry fixing groove 4, and the upper part of the gantry 1 is provided with a gantry screw hole; one end of the clamp body 6 is provided with a dovetail groove structure;

[0007] The top block 3 is arranged in the clamp body screw hole in the clamp body 6, and the pressure cover 5 is pressed tightly on the upper part of the clamp body 6;

[0008] Fixing of gantry tooling:

[0009] Use standard bolts to fix the gantry to the vibration table through the fixing slot 4 of the gantry to ensure the maximum rigid connection.

[0010] Adjust the angle of the clamp body 6 according to the blade body torsion angle requirement and place it in the gantry, add the gland 5, screw the standard bolts into the gantry screw holes, align with the positioning grooves of the gland 5, and complete the installation of the clamp body;

[0011] Clamp body fixation:

[0012] Push the bolt out from the top block outlet of the clamp body 6, and tighten the bolt with a torque wrench to fix the clamp body in the gantry 1. Installation of the blade:

[0013] Put the top block 3 into the screw hole behind the clamp body 6. When testing the blade, slide the blade through one end of the dovetail groove of the clamp body 6, align it with the exit position of the top block, and clamp the blade with limited force using a torque wrench.

[0014] Clamp body replacement or adjustment:

[0015] After completing the test, use a torque wrench to loosen the bolts at the back of the clamp, take out the test blade, loosen the standard bolts in the gantry screw holes, and make the clamp 6 adjustable or replaceable. For blades with different tenon structures, replace the clamp and repeat the above steps to complete the blade clamping. For blades with the same tenon structure, just adjust the angle of the clamp 6 according to the blade body torsion angle requirement and repeat the above steps to complete the blade clamping again.

[0016] Compared with the prior art, the present invention has the following advantages:

[0017] The universal aero-engine blade test clamping device and method described in the present invention meet the test requirements, ensure the quality of the vibration test, have completed the scientific research test verification, and achieved the expected effect. It greatly shortens the relevant blade vibration test cycle and reduces the test cost. At the same time, it expands the design ideas of the vibration test compressor blade clamping device. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] The present invention is further described in detail below in conjunction with the accompanying drawings and embodiments:

[0019] Figure 1 This is a schematic diagram of a general-purpose aircraft engine blade test clamping device. DETAILED DESCRIPTION

[0020] The present invention will be further explained below in conjunction with specific implementation plans, but the present invention is not limited thereto. The structures, proportions, sizes, etc. illustrated in the drawings of the specification are only used to match the contents disclosed in the specification for people familiar with this technology to understand and read, and are not used to limit the restrictive conditions under which the present invention can be implemented. Therefore, they have no substantive technical significance. Any structural modification, change in proportional relationship or adjustment of size should still fall within the scope of the technical content disclosed by the present invention without affecting the effects and purposes that can be achieved by the present invention.

[0021] The present invention provides a universal aircraft engine blade test clamping device and method, which is characterized by:

[0022] The universal aircraft engine blade test clamping device comprises a gantry 1, a pressure cover 5, a top block 3, and a clamp body 6. The lower side of the gantry 1 is provided with a gantry fixing groove 4, and the upper part of the gantry 1 is provided with a gantry screw hole; one end of the clamp body 6 is provided with a dovetail groove structure;

[0023] The top block 3 is arranged in the clamp body screw hole in the clamp body 6, and the pressure cover 5 is pressed tightly on the upper part of the clamp body 6;

[0024] Fixing of gantry tooling:

[0025] Use standard bolts to fix the gantry to the vibration table through the fixing slot 4 of the gantry to ensure the maximum rigid connection.

[0026] Adjust the angle of the clamp body 6 according to the blade body torsion angle requirement and place it in the gantry, add the gland 5, screw the standard bolts into the gantry screw holes, align with the positioning grooves of the gland 5, and complete the installation of the clamp body;

[0027] Clamp body fixation:

[0028] Push the bolt out from the top block outlet of the clamp body 6, and tighten the bolt with a torque wrench to fix the clamp body in the gantry 1. Installation of the blade:

[0029] Put the top block 3 into the screw hole behind the clamp body 6. When testing the blade, slide the blade through one end of the dovetail groove of the clamp body 6, align it with the exit position of the top block, and clamp the blade with limited force using a torque wrench.

[0030] Clamp body replacement or adjustment:

[0031] After completing the test, use a torque wrench to loosen the bolts at the back of the clamp, take out the test blade, loosen the standard bolts in the gantry screw holes, and make the clamp 6 adjustable or replaceable. For blades with different tenon structures, replace the clamp and repeat the above steps to complete the blade clamping. For blades with the same tenon structure, just adjust the angle of the clamp 6 according to the blade body torsion angle requirement and repeat the above steps to complete the blade clamping again.

[0032] Matters not covered by the present invention are known technologies.

[0033] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A universal aircraft engine blade test clamping device, characterized in that: include, The gantry (1), the pressure cover (5), the top block (3), and the clamp body (6) are composed of four parts; the lower side of the gantry (1) is provided with a gantry fixing groove (4), and the upper part of the gantry (1) is provided with a gantry screw hole; the center of the clamp body (6) is provided with a clamp body screw hole and a top block outlet, and the top block outlet end is provided with a dovetail groove structure; The top block (3) is arranged in the screw hole of the clamp body (6), and the pressure cover (5) is pressed tightly on the upper part of the clamp body (6); the gantry tooling is fixed: the gantry is fixed to the vibration table surface by using standard bolts through the fixing grooves (4) of the gantry to ensure the maximum rigid connection.

2. A method for holding a universal aircraft engine blade test clamping device as claimed in claim 1, characterized in that: The following steps are involved: Specific installation: Adjust the angle of the clamp body (6) according to the blade body torsion angle requirement and place it in the gantry, add the gland (5), screw the standard bolts into the gantry screw holes, align with the positioning grooves of the gland (5), and complete the installation of the clamp body; Clamp body fixation: Push the bolt out from the ejector block outlet of the clamp body (6), and tighten the bolt with a torque wrench to complete the fixation of the clamp body in the gantry (1). Installation of blades: Put the top block (3) into the screw hole at the rear of the clamp body (6). When testing the blade, slide the blade through one end of the dovetail groove of the clamp body (6), align it with the top block outlet position, and use a torque wrench to clamp the blade with limited force. Clamp body replacement or adjustment: After the test is completed, the rear bolts of the clamp body are loosened with a torque wrench, the test blade is taken out, and the standard bolts in the gantry screw holes are loosened to make the clamp body (6) adjustable or replaceable. For blades with different tenon structures, the clamp body is replaced and the above steps are repeated to complete the blade clamping. For blades with the same tenon structure, the angle of the clamp body (6) only needs to be adjusted according to the blade body torsion angle requirement and the above steps are repeated to complete the blade clamping again.

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