A Reliability Analysis Method of Turbine Disk Partition Based on Size Effect Correction

A size effect and analysis method technology, applied in special data processing applications, instruments, geometric CAD, etc., can solve the problems that it is difficult to accurately give the actual life of the structure and quantify the failure of the structure, and achieve accurate turbine disk life and reliability, quantification The effect of risk of failure

Active Publication Date: 2019-03-22
BEIHANG UNIV
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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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  • A Reliability Analysis Method of Turbine Disk Partition Based on Size Effect Correction
  • A Reliability Analysis Method of Turbine Disk Partition Based on Size Effect Correction
  • A Reliability Analysis Method of Turbine Disk Partition Based on Size Effect Correction

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Embodiment Construction

[0014] The technical scheme of the reliability analysis of the turbine disk partition based on the size effect correction of the present invention will be further described below in conjunction with the accompanying drawings.

[0015] Consider the dispersion of factors such as materials and geometric dimensions, and carry out regional division and combined risk assessment on the turbine disk, combined with the life reliability analysis method of the turbine disk structure, the process is shown in figure 1 .

[0016] (1) Remove the small chamfers and bosses on the turbine disk to simplify the turbine disk model; conduct Latin hypercube sampling on all the geometric dimensions of the simplified turbine disk, generate samples of different geometric dimensions for finite element analysis, and use turbine The maximum equivalent stress of the disk is used as the output response, and a quadratic polynomial without cross terms is constructed as the response surface model, and its func...

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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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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F17/50
CPCG06F30/15G06F30/17G06F30/23G06F2119/04G06F2119/06
Inventor 王荣桥胡殿印胡如意刘茜
Owner BEIHANG UNIV
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