Life assessment method, device, equipment and media of aeroengine turbine blades
A technology for aero-engines and turbine blades, applied in the aviation field, can solve problems such as slow interpolation of fluid and solid data, inability to directly give life spans, lack of constitutive equations of turbine blades, etc., to achieve high accuracy, increase speed, and improve accuracy Effect
Active Publication Date: 2022-04-29
NORTHWESTERN POLYTECHNICAL UNIV
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Problems solved by technology
[0003] Based on the current fluid-solid coupling, a large number of file formats need to be converted, the fluid-solid data interpolation is slow, the constitutive equation describing the turbine blade is lacking, and the life span cannot be directly given. This application provides an aero-engine turbine blade. Lifetime assessment method, electronic device and storage medium
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[0042] In order to make the above-mentioned purpose, features and advantages of the present application more obvious and understandable, the specific implementation manners of the present application will be described in detail below in conjunction with the accompanying drawings. In the following description, numerous specific details are set forth in order to provide a thorough understanding of the application. However, the present application can be implemented in many other ways different from those described here, and those skilled in the art can make similar improvements without departing from the connotation of the present application, so the present application is not limited by the specific implementation disclosed below.
[0043] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the technical field to which this application belongs. The terms used herein in the specificatio...
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The present application relates to a life assessment method, device, equipment and medium of an aeroengine turbine blade. The method includes: obtaining a fluid calculation result file and a solid calculation file to be interpolated; extracting information in the fluid calculation result file, and identifying the solid calculation to be interpolated The file type of the file and extract the information of the solid calculation file to be interpolated; without changing the file type of the solid calculation file to be interpolated, the information in the fluid calculation result file and the information of the solid calculation file to be interpolated are interpolated The interpolation result is obtained; the constitutive model calculates the interpolation result to obtain the stress value of the blade; the life of the blade is estimated according to the stress value of the blade. This application interpolates without changing the file type of the solid calculation file to be interpolated. Since there is no intermediate format conversion, the interpolation speed is improved and the error is reduced. The stress value of the blade is calculated according to the constitutive model. According to the stress value of the blade The method for evaluating the life of the blade is quick and accurate.
Description
technical field [0001] The present application relates to the field of aviation technology, in particular to a method, device, equipment and medium for evaluating the life of an aeroengine turbine blade. Background technique [0002] Aeroengines are one of the most technically demanding products in the world, representing the highest industrial level of a country. The working environment of turbine blades is extremely harsh, and they need to withstand the combined effects of high temperature, high pressure, rotating centrifugal force and vibration. In the development process of a new engine, the calculation process of the strength and life of its core component - the single crystal turbine cooling blade is very cumbersome and requires a lot of time and effort. In the design of aero-engines, it is also necessary to integrate the knowledge of various disciplines such as fluid-solid heat, which is an extremely complex and systematic process. And experimenting with turbine bla...
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IPC IPC(8): G06F30/17G06F119/14G06F119/04G06F113/08
CPCG06F30/17G06F2119/14G06F2119/04G06F2113/08
Inventor 温志勋程浩赵彦超杜建冲钟宇豪朱西点朱江辉岳珠峰
Owner NORTHWESTERN POLYTECHNICAL UNIV