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Probabilistic life prediction method for blade vibration fatigue

A vibration fatigue, probabilistic life technology, applied in geometric CAD, sustainable transportation, special data processing applications, etc., can solve the problem of low confidence level, distribution type assumptions and testing influence, and probability life prediction results without confidence interval estimation and other problems, to achieve the effect of high computational efficiency, computational accuracy and high confidence level

Active Publication Date: 2020-04-24
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

[0005] Existing methods have the following three disadvantages: (1) Using traditional probability distribution type assumptions and parameter estimation methods, the calculation results are greatly affected by artificial distribution type assumptions and tests; (2) The calculation accuracy of the proxy model is limited by the sample Influenced by the number of samples, if the number of samples is insufficient or the local functional relationship changes drastically, the calculation accuracy of the proxy model will not be high; (3) the confidence interval has not been estimated for the probabilistic life prediction results, and the confidence level is low

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  • Probabilistic life prediction method for blade vibration fatigue
  • Probabilistic life prediction method for blade vibration fatigue
  • Probabilistic life prediction method for blade vibration fatigue

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Embodiment Construction

[0046] The blade vibration fatigue probabilistic life prediction model and method provided by the present invention comprise the following steps:

[0047] 1) Establish material C-P-S-N fatigue curve model

[0048] Due to the limited number of fatigue tests at the same stress level, the estimated probability distribution parameters (lognormal distribution parameters) are different from the parent distribution parameters. In order to improve the confidence level of fatigue life estimation, the dispersion coefficient method was introduced to establish the C-P-S-N fatigue curve model.

[0049] Assuming that the fatigue life sample group X of a certain stress level obeys the logarithmic normal distribution, then the random variable Y=lgX obeys the normal distribution N(μ Y ,σ Y ); define F- 1 (μ Y ,σ Y ,1-p) is the quantile value (F -1( ) is the inverse function of the cumulative distribution function of the random variable Y), then the fatigue life corresponding to the relia...

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Abstract

The invention provides a method for predicting blade vibration fatigue probability life. The method comprises the steps of (1) establishing a C-P-S-N fatigue curve model of a material; (2) establishing a dual maximum entropy tantile function model; and (3) establishing a blade vibration fatigue probability life prediction model and a blade vibration fatigue probability life prediction method based on the C-P-S-N fatigue curve model and the dual maximum entropy tantile function model. The blade vibration fatigue probability life prediction model and the blade vibration fatigue probability life prediction method established by the invention can be successfully applied to prediction of blade vibration fatigue probability life of an aircraft engine. Compared with an existing prediction method, the method for predicting the blade vibration fatigue probability life has the advantages of high calculation accuracy, confidence level and calculation efficiency.

Description

technical field [0001] The invention relates to vibration fatigue life prediction of aerostructure parts, in particular to vibration fatigue probabilistic life prediction of aeroengine blades. Background technique [0002] Blades are an important part of an aero-engine. The engine relies on the blades to compress and expand the gas to generate powerful power to propel the aircraft forward. When the blade is working, it bears high centrifugal load, aerodynamic load, vibration alternating load, etc., and it is prone to failure. Among the structural failures of the engine, the proportion of blade failure is quite high, which seriously affects the safety of the engine. In the aero-engines produced in my country around the 1970s, fatigue failure caused by blade vibration was particularly common, accounting for about 25% of blade failure accidents. With the emergence of modern high-thrust, high-thrust ratio, high-bypass ratio engines, the problem of blade vibration fatigue has b...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F30/17
CPCG06F30/17Y02T90/00
Inventor 温卫东吴福仙翁晶萌陈波
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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