Aeroengine blade vibration test device and method

Abstract

The invention relates to an aeroengine blade vibration test device, and belonging to the technical field of engine blade test devices. The aeroengine blade vibration test device comprises a device main body arranged on a shaking table, wherein a rotating disc for inserting blades is arranged outside the device main body; a rear cover for driving the rotating disc to rotate is arranged inside the device main body; a rotating disc is arranged on one side of the rear cover, and a clamping disc is arranged on the other side of the rear cover; a rear cover chamber passing through a pressing block is arranged along the height direction of the rear cover; and the rotating disc is provided with a rotating disc chamber communicating with the rear cover chamber and a mortise groove for inserting blades. The aeroengine blade vibration test device is suitable for testing blades of various structures, can realize vibration tests of the blades at any angle, and has high test accuracy and accuracy.

Description

technical field [0001] The invention relates to a vibration test device for aeroengine blades, belonging to the technical field of engine blade test devices. Background technique [0002] Blades are one of the important parts of aero-engines, mainly used in compressors and gas turbines. Among them, the compressor blades are not only subject to high centrifugal load, aerodynamic load, atmospheric temperature difference load and vibration alternating load, but also are impacted by foreign objects in the engine intake passage, and are eroded by wind, sand and humidity. Turbine blades not only bear the corrosion and erosion caused by high temperature, but also bear the huge centrifugal force, aerodynamic force and vibration load caused by high-speed rotation. It can be seen that the working condition of the blade is very bad, and it is one of the main parts that determine the life of the engine. Therefore, the blade must go through vibration assessment, function assessment and...

AI Technical Summary

Problems solved by technology

[0004] 1. The compressor and gas turbine in the aero-engine cover multi-stage blades. Among them, the compressor blades mainly use dovetail-shaped tenons, and the turbine blades mainly use fir tree-shaped tenons. The structural parameters of different blade tenons are different. Therefore, the blade vibration test test The test device is required to be able to clamp blades of various specifications, but the traditional test device clamps blades with a single specification, which cannot meet the actual test requirements;

[0005] 2. The blade vibration test requires that the test device can measure the mode and response of the blade at any angle, but the traditional test device clamps the blade in a single direction, which cannot meet the test requirements;

[0006] 3. The existing test device cannot realize the vibration test of the blade at any angle, and the design of the briquetting block cannot rotate with the change of the test angle, which cannot guarantee the pre-tightening force of the blade during the test

[0007] The above deficiencies lead to time-consuming, labor-intensive and high-cost test of blade vibration test, and low test efficiency. Therefore, there is an urgent need for an aero-engine blade vibration test device that can solve the above technical problems.

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