Turbine disk partitioning reliability analysis method based on size effect modification

Abstract

The invention relates to a turbine disk partitioning reliability analysis method based on size effect modification. The method includes the steps of firstly, simplifying a turbine disk model, analyzing the sensitivity to obtain the key geometrical size of a turbine disk, measuring the key geometrical size of the turbine disk to obtain a corresponding probability distribution feature; secondly, obtaining the material attributes of the turbine disk, and establishing a SWT probability cyclic stress-strain relation model and a strain-life model of the turbine disk; thirdly, conducting geometricalparameterization modeling on the turbine disk, analyzing finite elements, dividing areas according to the stress level and temperature distribution conditions of the turbine disk, conducting Latin hypercube sampling on the established SWT probability cyclic stress-strain relation model and the probability strain-life model to obtain the relation between random input variables and output service lives of all divided areas of the turbine disk and establish response face models, and sampling the response face models of all the divided areas through a Monte-Carlo sampling method to obtain the corresponding service life distribution and finally obtain the fatigue life and reliability of the turbine disk; fourthly, conducting size effect modification on the service life distribution of the turbine disk.

Description

technical field [0001] The invention relates to a reliability design method aiming at the structural life of an aeroengine turbine disc, which is a design method capable of considering the dispersion and size effects of factors such as materials and geometry, 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). At present, the structure of active and in-service engines is heavy (performance is not enough) and reliability is not guaranteed. The reason is that in the design process, some parts of the structure are conservatively designed, which will...

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Problems solved by technology

[0004] At present, the traditional turbine disk structure design method is mainly based on deterministic design, combined with some experimental content, it is difficult to accurately give the actual life of the structure and quantify the failure risk of the structure

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