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An aero-engine turbine blade reliability digital twinning modeling method

A technology for aero-engines and turbine blades, applied in electrical digital data processing, special data processing applications, instruments, etc., can solve problems such as difficult to meet the real-time state evaluation and reliability prediction of turbine blades, to improve accuracy and credibility, The effect of reducing uncertainty and improving fidelity

Pending Publication Date: 2021-03-16
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Application Information

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Problems solved by technology

Existing technologies are difficult to meet the needs of real-time state assessment and individual reliability prediction of turbine blades in a dynamic environment

Method used

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  • An aero-engine turbine blade reliability digital twinning modeling method
  • An aero-engine turbine blade reliability digital twinning modeling method
  • An aero-engine turbine blade reliability digital twinning modeling method

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Embodiment Construction

[0034] In order to enable those skilled in the art to better understand the technical solutions of the present invention, the present invention will be further described in detail below in conjunction with specific embodiments.

[0035] The embodiment of the present invention provides a digital twin modeling method for the reliability of an aeroengine turbine blade, the flow chart is as follows figure 1 shown, including:

[0036] S1. Obtain the relevant data of a certain type of aeroengine cycle reference point (take-off condition under standard day conditions) and non-design points (flight conditions under actual operating data and test data), including: 1) given flight conditions and atmospheric conditions, flight altitude, flight Mach number, atmospheric temperature, atmospheric pressure and atmospheric humidity; 2) Under given flight conditions and atmospheric conditions, the performance requirements of the engine, such as thrust, unit thrust and unit fuel consumption rate...

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Abstract

The invention discloses an aero-engine turbine blade reliability digital twinning modeling method, relates to the technical field of aero-engines, and aims to realize high fidelity simulation and tracking of aero-engine turbine blade damage and life loss and quickly and efficiently evaluate the reliability and residual life of the aero-engine turbine blade. According to the invention, the turbineblade is taken as an object, aiming at the characteristics of multi-source and multi-time-scale use reliability related information, few fault samples and the like of the turbine blade, a physical model driving and data driving fusion method is adopted, that is, the specialty of a physical model in the aspect of explaining specific data is fully utilized, and a turbine blade digital entity model based on a high-precision physical model and multi-source data is constructed by means of the advantages of a machine learning method in the aspects of dimension reduction and multi-modal data fitting.The model can reflect the physical characteristics of the turbine blade and the variable characteristics dealing with different environments and damages, and can realize the product operation reliability dynamic evaluation and residual life prediction of multimode information fusion.

Description

technical field [0001] The invention relates to the technical field of aero-engines, in particular to a reliability digital twin modeling method for turbine blades of an aero-engine. Background technique [0002] Turbine blades are one of the key rotating parts of aero-engines. They work under conditions of high temperature, high pressure, high speed, and alternating loads for a long time. Their actual service life depends not only on the design, manufacturing, and process levels, but also on the actual operation The environment, usage and maintenance are closely related. The reliability of turbine blades is directly related to the reliability, economy and life of the engine, and has an important impact on the safety and economy of the engine. Therefore, establishing a high-fidelity turbine blade reliability evaluation model is of great significance for reducing engine maintenance support costs and improving utilization. [0003] At present, the reliability modeling method...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/15G06F30/17G06F30/27G06F119/02
CPCG06F30/15G06F30/17G06F30/27G06F2119/02Y02T90/00
Inventor 孙见忠刘赫雷世英宁顺刚易杨
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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