The profiling repair method of the blade tip wear of the compressor rotor blade

Abstract

The invention provides a profiling repair method of an abraded blade tip of a rotor blade of a gas compressor. The method comprises the following steps: carrying out local heating and superfast cooling on abraded parts of the blade tip of the rotor blade so as to carry out laser cladding repairing in a coaxial powder conveying manner under the protection of a non-environmental box by taking high-temperature nickel-based alloy powder for forming the body of the rotor blade of the gas compressor as a cladding material, wherein in the laser cladding process, the laser cladding on parts with different cross section sizes, of the blade tip is carried out by regulating the laser power of a laser in different cladding areas according to the width measurement result of the cross section of the blade tip of the rotor blade; setting the change range of the laser power within 100W to 300W, feeding argon from an argon inlet in a radial direction of a cover body of a protective gas cover and discharging the argon from an argon outlet in the bottom of the cover body of the protective gas cover so as to form a protective gas curtain; carrying out cladding on areas with the width less than 0.5mm, at a gas inlet and a gas outlet of the blade tip, by virtue of a low laser power between 100W and 120W; and carrying out cladding on the other areas with the width greater than or equal to 0.5mm, of the blade tip, by virtue of a high laser power between 240W and 300W. The method is low in repair cost, and the repaired blade tip is long in service life.

Description

Technical field [0001] The invention relates to a method for repairing abrasion of the blade tip of a rotor blade of an aeroengine high-pressure compressor. In particular, it is a method for repairing the wear of high-pressure compressor rotor blade tips made of high-temperature alloy GH4169. technical background [0002] The clearance between the tip of the rotor blade of the aero-engine compressor and the casing is an important indicator of engine performance. Excessive clearance results in leakage and instability of the tip airflow, and the engine efficiency is significantly reduced. If the clearance is too small, it is easy to cause the frictional collision between the rotor and the casing to cause the blade to break. Therefore, maintaining a proper clearance is very important for the engine. The overhaul inspection results of the aero-engine after 300 hours of operation showed that the high-pressure compressor rotor blade tip was severely worn, and the 5th to 8th stage bl...

AI Technical Summary

Problems solved by technology

The repair of the worn part of the blade tip of the high-pressure compressor rotor adopts conventional argon arc welding and other methods, which will cause a large thermal impact on the substrate and affect the performance of the compressor rotor blade

At the same time, the profile of the compressor rotor blade is complex, and it is difficult to achieve profiling repair by manual welding, and the thickness of the intake and exhaust edges is only 0.35mm to 0.50mm, and undercutting is prone to occur during manual welding

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