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Turbine shaft reliability optimization design method based on Kriging model

A technology for optimizing design and reliability, applied in design optimization/simulation, sustainable transportation, instruments, etc., can solve problems such as long time-consuming and large amount of calculation

Active Publication Date: 2020-10-16
NORTHWESTERN POLYTECHNICAL UNIV
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  • Description
  • Claims
  • Application Information

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Problems solved by technology

The most challenging problem in reliability optimization design is that the reliability constraint function is a "black box" function, and the simulation analysis process requires a large amount of calculation and takes a long time

Method used

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  • Turbine shaft reliability optimization design method based on Kriging model
  • Turbine shaft reliability optimization design method based on Kriging model
  • Turbine shaft reliability optimization design method based on Kriging model

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Embodiment Construction

[0038] 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 will fully convey the concept of example embodiments to those skilled in the art. The described features, structures, 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 present disclosure.

[0039] In the drawings, the thicknesses of regions and layers may be exaggerated for clarity. The same reference numerals in the drawings denote the same or similar structures, and thus their detailed descriptions will be omitted.

[0040] The described features, structures, or characteristic...

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Abstract

The invention provides a turbine shaft reliability optimization design method based on a Kriging model. The turbine shaft reliability optimization design method comprises the steps of establishing a turbine shaft parameterized finite element simulation model is established; determining a turbine shaft failure mode, and establishing a target function and a reliability constraint function of the turbine shaft; determining an iterative design point and an iterative most possible failure point; constructing a Kriging agent model of the reliability constraint function; identifying an important failure mode by adopting an adaptive learning function to carry out adaptive sampling, and updating the Kriging agent model; solving by using a single-layer method to obtain a current optimization designpoint and a current most possible failure point; comparing the current optimization design point with the iterative design point, and if | | the current optimization design point-the iterative designpoint | is less than or equal to a threshold, determining the current optimization design point as a determined optimization design point; otherwise, updating the iterative design point by using the current optimization design point, and updating the iterative most probable failure point by using the current most probable failure point. The method is small in calculation scale and short in consumed time, and has very strong engineering significance for turbine shaft reliability optimization design.

Description

technical field [0001] The disclosure relates to the field of reliability analysis, in particular to a Kriging model-based reliability optimization design method for a turbine shaft, a computer storage medium and electronic equipment. Background technique [0002] The turbine shaft is an important component in the hot end of a turbine engine. It plays a supporting role in the structure of the aero-engine, supporting the turbine rotor components on the low-pressure turbine shaft; at the same time, it also plays a role in transmitting power, and transmits power to other components installed on it through the rotation of the low-pressure turbine shaft. The performance requirements of modern military aircraft engines are constantly increasing, and higher requirements are also imposed on their reliability. With the help of high-performance computers, simulation analysis of various performance indicators of products has become a necessary means in the design process of aviation pr...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/17G06F30/20G06F119/02
CPCG06F30/17G06F30/20G06F2119/02Y02T90/00
Inventor 周易成吕震宙
Owner NORTHWESTERN POLYTECHNICAL UNIV
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