Method for predicting residual life of digital twin-driven aero-engine turbine disc

Abstract

The invention discloses a method for predicting the residual life of a turbine disc of a digital twin-driven aero-engine. The method comprises the following steps: firstly, simulating a vibration signal of an aero-engine turbine disc by utilizing digital twinning of the aero-engine turbine disc; extracting radial displacement, blade circumferential displacement and blade spacing information of theaero-engine turbine disc; extracting aero-engine turbine disc radial displacement, blade circumferential displacement and blade spacing information from the aero-engine turbine disc actual measurement vibration signals subjected to noise reduction processing by using the same extraction method; and calculating a difference value between the aero-engine turbine disc damage model and the aero-engine turbine disc, adjusting and correcting internal parameters of the aero-engine turbine disc damage model by utilizing a difference value calculation result, and finally calculating the residual lifeof the aero-engine turbine disc by utilizing the updated aero-engine turbine disc damage model. According to the digital twin-driven aero-engine turbine disc residual life prediction method provided by the invention, the working condition change of the aero-engine turbine disc can be considered, so that an accurate life prediction result is obtained.

Description

technical field [0001] The invention belongs to the field of mechanical life prediction, and in particular relates to a method for predicting the remaining life of an aeroengine turbine disc driven by a digital twin. Background technique [0002] Aeroengine turbine disk is a key part of durability and fracture of aeroengine, and it plays a role in converting high-temperature and high-pressure gas flowing out of the combustion chamber into mechanical energy in aeroengine. The working environment of the aero-engine turbine disk is harsh, and it is subjected to various loads such as large centrifugal load and temperature load. The safe operation of aero-engines poses a huge threat. The existing remaining life prediction technology of aero-engine turbine discs is not mature enough. During the service process of aero-engines, aero-engine turbine discs will experience continuous starting, stopping, and various changes in operating speed, operating temperature, and working load fr...

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Problems solved by technology

[0005] In order to solve the above problems, the present invention provides a digital twin-driven aero-engine turbine disk remaining life prediction method, which solves the problem that the model in the existing aero-engine turbine disk remaining life prediction method is only applicable to a single working condition, and insufficient consideration is given to changes in working conditions. The problem of inaccurate remaining life prediction results

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