Method and system for measuring concentricity and tip clearance of rotor and stator of aero-engine

Abstract

Disclosed are a method and system for measuring concentricity and the tip clearance of a rotor and a stator of an aero-engine. The method comprises the steps that the clearance amount of the rotor and the stator of the aero-engine at an initial measurement point is acquired; a clearance maximum jerk value FIR value, the phase of the clearance maximum jerk value FIR value, a maximum deviation IMP value between a sampling profile curve concave point and a mean profile, the phase of the maximum deviation IMP value, an eccentric distance ECC value, the phase of the eccentric distance ECC value, a maximum clearance value relative to the rotation center, the phase of the maximum clearance value, a minimum clearance value relative to the rotation center, the phase of the minimum clearance value, a maximum clearance value relative to the geometric center, the phase of the maximum clearance value, a minimum clearance value relative to the geometric center and the phase of the minimum clearance value are obtained; an angle-clearance distribution diagram is drawn; the clearance amount is corrected in the horizontal placement measurement process; a concentricity error value and the tip clearance of the rotor and the stator of the aero-engine are obtained. The system comprises a sampled data analysis module, a rotor and stator concentricity calculation module, a tip clearance analysis and calculation module and a horizontal-measurement deflection correction module. The method and system are suitable for measuring the concentricity and the tip clearance of the rotor and the stator of the aero-engine.

Description

technical field

[0001] The invention belongs to the technical field of aero-engines, and in particular relates to a method and system for measuring the concentricity of an aero-engine rotor and a stator and blade tip clearance. Background technique

[0002] The fan (low-pressure compressor), high-pressure compressor, high-pressure turbine and low-pressure turbine of the aero-engine are the four major rotors of rotating machinery, and the corresponding supporting structure is the key structure of the engine, which has great influence on the performance, safety and life of the engine. The important influence needs to be paid attention to and detected during the assembly process. Among the various measurement parameters, the concentricity is one of the key characteristic parameters reflecting the design and assembly structure state and the quality of the rotating support. It directly affects the rotor tip clearance at all levels. Etc., have a great impact on engine performance....

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