Aero-engine turbine blade reliability evaluation method based on fracture mechanics

Abstract

The invention discloses an aero-engine turbine blade reliability evaluation method based on fracture mechanics. The method comprises the following steps: S1, establishing a simplified model of a bladesection by taking a turbine blade as a research object, calculating a stress intensity factor of the turbine blade containing an initial I-type crack at a blade root by applying a finite element method, substituting the stress intensity factor into a shape factor calculation formula, and determining a shape factor parameter; S2, establishing a turbine blade reliability model based on the generalized stress intensity interference model; and S3, establishing a probability density function of load and fracture toughness, establishing a probability life model and a reliability model for the bladein combination with a Paris formula, and solving the model to obtain the change condition of the reliability of the turbine blade along with the life. According to the method, initial defects existing in the blade are considered, on the basis of the initial defects, the crack propagation life of the I-shaped cracks on the surface of the blade under the cyclic load is established, and life prediction and reliability evaluation of the blade can be more accurate.

Description

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AI Technical Summary

Benefits of technology

This technology helps evaluate how well a specific type of material works over time by considering its potential failures caused during use or stressing it repeatedly. By comparing different types of materials together, we aimed at finding ways to improve their durability against these issues.

Problems solved by technology

The technical problem addressed in this patents relates to accurately estimating the lifetime of aerospace engine components such as airfoils (aerial fans) during their lifespan due to flaws caused by external environmental conditions like rainwater hitting the surfaces with small holes called microscopically rough spots. Current methods involve calculating the remaining time from failures before reaching critical points, assessing the risk of breakage, taking precautions against potential issues associated with ingestable debris, and studying the effectiveness of various materials used in aircraft engines over time.

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