A method for replacing aircraft engine blades

Abstract

The invention relates to a method for replacing blades of an aircraft engine. The method comprises the following steps: cutting off the blades on a low-pressure turbine guider welding assembly; modifying the shape of the replacement blades according to the shape of the welding assembly; assembling the modified replacement blades into the cut low-pressure turbine guider welding assembly to performwelding and positioning; after the replacement blades are completely welded and fixed on the low-pressure turbine guider welding assembly, performing a turn-milling on the end face of the boss of thereplacement blades, and performing a location hole finish machining on the replaced blades; after the location hole finish machining is completed, polishing the parts of the replacement blades which are welded with the front piece and the tail piece of an upper edge plate and a flow deflector until the metal luster is exposed; welding the flow deflector, the front piece, and the tail piece to theupper edge plate of the replacement blades by using a point welding machine. According to the method for replacing blades of the aircraft engine, targeted replacement can be performed on the guide blades of an aero-engine, and the maintenance cost of the engine is reduced.

Description

technical field [0001] The invention relates to the technical field of maintenance of aircraft engine blades, in particular to a method for replacing aircraft engine blades. Background technique [0002] The guide vane is the most severe part of the aero-engine to withstand high temperature and thermal shock, so the guide vane is very easy to damage, especially in the working process of the aero-engine and gas turbine, the engine turbine guide due to the local high temperature on the surface, the turbine guide vane Under the action of thermal shock, gas corrosion and vibration load, the blades will be ablated and form faults, which will affect the reliable operation of the engine. In order to ensure the safe use of the engine, it is necessary to replace the faulty blades that have occurred. At present, there is no method for repairing and replacing the blades, which makes the maintenance cost of the guide blades of the aero-engine relatively high. Contents of the invention...

AI Technical Summary

Problems solved by technology

[0002] The guide vane is the most severe part of the aero-engine to withstand high temperature and thermal shock, so the guide vane is very easy to damage, especially in the working process of the aero-engine and gas turbine, the engine turbine guide due to the local high temperature on the surface, the turbine guide vane Under the action of thermal shock, gas corrosion and vibration load, the blades will be ablated and form faults, which will affect the reliable operation of the engine

In order to ensure the safe use of the engine, it is necessary to replace the faulty blades that have occurred. At present, there is no method for repairing and replacing the blades, which makes the maintenance cost of the guide blades of the aero-engine relatively high.

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