A Design Method for Vibration Reliability of Turbine Blisk Structure

Abstract

The invention discloses a design method of the vibration reliability of a turbine leaf disc structure. The design method comprises the following steps: designing an initial scheme, determining the geometrical shape of the structure, and calculating weight; drawing a Campbell drawing, and taking a deterministic avoidance resonance margin as an optimization constraint condition; analyzing geometries, materials and the like which affect the turbine leaf disc structure, obtaining the rotation speed spectrum of an engine through the original flight parameter record and the load spectrum analysis of the engine, and obtaining the reliability degree of the avoidance resonance margin given by a deterministic design criteria; aiming at a structure vibration probability criteria to evaluate a vibration reliability analysis result, and returning to design support if a structure reliability result does not meet requirements; analyzing each dangerous mode of vibration, carrying out combined risk evaluation on all modes of vibration, and calculating the turbine leaf disc structure to meet the reliability of the given avoidance resonance margin; and judging whether the reliability meets the requirements of each technical index or not, transferring into the design support if the reliability does not meet the requirements of each technical index, and revising dimensions or materials.

Description

technical field [0001] The invention relates to a reliability design method for the structural vibration of an aeroengine turbine blisk, which is a design method capable of considering the dispersion of factors such as material, geometry, and load, and belongs to the technical field of aerospace engines. Background technique [0002] Aeroengine is an extreme product, working under complex loads / environments such as high temperature, high pressure, and high speed; the improvement of engine performance and safety indicators requires the engine to be light in weight, long in life, and high in reliability (for example, for safe flight Engine structural parts require a low probability of failure, up to 10 -5 -10 -7 times / flight hour). Blade vibration fatigue damage faults in aero-engines are frequent and common faults, and their fault ratio often accounts for 30% to 40% of fatigue faults of engine parts. At present, the vibration problem is still one of the main problems plagu...

AI Technical Summary

Problems solved by technology

At the same time, since the dispersion of materials, geometry, and rotational speed is not considered in the structural design process, the risk of structural resonance cannot be quantified, and it cannot be guaranteed that the turbine blades will completely avoid the resonance state during flight.

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