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Proxy model-based fatigue creep life reliability optimization method for double-amplitude turbine disc

A fatigue creep and proxy model technology, applied in the field of aero-engines, can solve problems such as long time-consuming and large amount of calculation

Active Publication Date: 2021-11-09
NORTHWESTERN POLYTECHNICAL UNIV
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Problems solved by technology

[0003] The existing double-spoke turbine disk life reliability structural design is very little, and the existing turbine disk structural design method requires a large amount of calculation and takes a long time in the analysis process

Method used

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  • Proxy model-based fatigue creep life reliability optimization method for double-amplitude turbine disc
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  • Proxy model-based fatigue creep life reliability optimization method for double-amplitude turbine disc

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[0059] Example embodiments will now be described more fully with reference to the accompanying drawings. Example embodiments may, however, be embodied in many forms and should not be construed as limited to the examples set forth herein; rather, these embodiments are provided so that this disclosure will be thorough and complete and fully convey the concept of example embodiments to those skilled in the art.

[0060] Furthermore, the described features or characteristics may be combined in any suitable manner in one or more embodiments. In the following description, numerous specific details are provided in order to give a thorough understanding of embodiments of the invention. However, those skilled in the art will appreciate that the technical solutions of the present invention may be practiced without one or more of the specific details, or other methods, steps, etc. may be employed. In other instances, well-known methods have not been shown or described in detail to avoi...

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Abstract

The invention provides a proxy model-based double-amplitude turbine disc fatigue creep life reliability optimization method. The optimization method comprises the following steps of: establishing a geometric simulation model of a double-amplitude turbine disc; determining the relationship between the random variable and the fatigue creep life of the double-center-plate turbine disc; establishing a fatigue creep life reliability optimization design model of the double-center-plate turbine disc; adopting an adaptive Kriging approximation model to construct a Kriging approximation proxy model with reliability constraint and objective function convergence in the expansion space; determining an inverse design point under given design parameters and reliability indexes, performing local sampling at the inverse design point, and updating the convergent reliability constraint and the Kriging approximation proxy model of the target function; converting a reliability optimization problem into a deterministic optimization problem by using a sequence optimization and reliability evaluation method to solve an optimal solution based on the obtained Kriging approximation agent model of the constraint function and the target function and the inverse design point; if it is judged that the optimal solution converges, outputting an optimization result.

Description

technical field [0001] The invention relates to the technical field of aero-engines, in particular to a method for optimizing the fatigue creep life reliability of a double-width turbine disk based on a surrogate model. Background technique [0002] Turbine disk is one of the main components of aero-engine. It works at high temperature and high speed, bears complex loads, and is in a harsh environment. Once a destructive failure occurs, it will lead to serious consequences. The life of the turbine disk largely determines the life of the aeroengine. Therefore, the reliability optimization design of the turbine disk can help engineering designers reasonably establish safety margins and control the impact of random parameters on its safety, so that the life prediction and reliability analysis of the turbine disk are more consistent with the actual performance. Therefore, the design parameters of the turbine disk with sufficient safety reliability and optimal performance can be...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/17G06F30/23G06F111/04G06F119/02G06F119/04
CPCG06F30/17G06F30/23G06F2111/04G06F2119/02G06F2119/04
Inventor 蒋霞吕震宙王璐周易成
Owner NORTHWESTERN POLYTECHNICAL UNIV
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