Turbine blade disc structure service life reliability design method

Abstract

The invention relates to a turbine blade disc structure service life reliability design method. An initial scheme for a turbine blade disc structure is determined according to a traditional strength and service life analysis method, a geometrical shape of the structure is determined and weight of the structure is calculated; determinacy load of the structure is acquired and detailed 3D stress / strain analysis is conducted; a determinacy design criteria is designated to be an optimized constraint condition, and the design is returned to design support when the result does not meet the criteria demand; influence of the turbine blade disc structure is analyzed and the turbine blade disc is partitioned; structure reliability under each failure mode is calculated and a service life reliability analysis result is evaluated with the combination of the service life probability criteria; the design support is required when the structure reliability result does not meet the criteria demand; combined risk evaluation is conducted to a risk level of each failure mode and overall failure probability of the turbine blade disc structure is calculated; each technical index is determined whether to meet demands; and design support is required when the demands are not met or modifications are conducted to the size or the material.

Description

technical field [0001] The invention relates to a reliability design method aimed at the structural life of an aeroengine turbine blisk, which is a design method capable of considering the dispersion 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 lead to dan...

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Problems solved by technology

[0004] At present, the traditional design method of turbine blisk structure 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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