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Digital Twin Modeling Method for Aeroengine Turbine Disk-Rotor-Support System

A technology of aero-engine and support system, applied in the fields of electrical digital data processing, instrumentation, geometric CAD, etc.

Active Publication Date: 2021-02-02
XI AN JIAOTONG UNIV
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  • Claims
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Problems solved by technology

In the actual operation process, the turbine disk-rotor-support system of the aeroengine works under the condition of multi-physics coupling, and at the same time it is affected by high temperature, high speed, and high load. Only a single physical model is considered, which will inevitably lead to inaccuracies sex

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  • Digital Twin Modeling Method for Aeroengine Turbine Disk-Rotor-Support System
  • Digital Twin Modeling Method for Aeroengine Turbine Disk-Rotor-Support System
  • Digital Twin Modeling Method for Aeroengine Turbine Disk-Rotor-Support System

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Embodiment Construction

[0033] The present invention will be described in detail below in conjunction with the accompanying drawings.

[0034] The existing modeling methods of the aero-engine turbine disc-rotor-support system are basically based on the optimization of a single physical model, but the aero-engine turbine disc-rotor-support system has been working for a long time under complex conditions coupled with multiple physical fields. Calculation results of physical models will inevitably have inaccuracies. In addition, the existing aeroengine turbine disk-rotor-support system model does not take into account the real-time changes in the working state of the turbine disk-rotor-support system. Since the flight speed, altitude and attitude will change continuously during the flight, the aviation The operating speed, temperature and load of the engine turbine disc-rotor-support system will also change continuously. Using a constant model to simulate the turbine disk-rotor-support system of an aer...

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Abstract

The invention discloses a digital twin modeling method for an aero-engine turbine disk-rotor-support system, based on the characteristics of the turbine disk-rotor-support system and its initial working conditions / environmental parameters and the physical relationship between the turbine disk / rotary shaft / main bearing The relationship between the establishment of a digital twin sub-model of the aero-engine turbine disc-rotor-support system; the establishment of a multi-physics integrated simulation platform with multiple sub-models, and the integration of the sub-models into a unified physical model; the establishment of a multi-physics integrated simulation platform Model; input the working conditions / environmental parameters of the aero-engine bearings into the unified physical model, compare and analyze the simulation calculation results with the measured signals after noise reduction feature extraction and processing, optimize the unified physical model, and obtain a real-time synchronized aero-engine The digital twin model of the turbine disk-rotor-support system; it can overcome the shortcomings of the existing modeling method that considers too many factors and does not consider real-time changes in operating conditions.

Description

technical field [0001] The invention belongs to the technical field of mechanical diagnosis intelligence and digitalization, and in particular relates to a digital twin modeling method of an aeroengine turbine disk-rotor-support system. Background technique [0002] Aeroengine is a typical high-speed rotating machinery, and it is an important standard to measure a country's technological level, military strength and comprehensive national strength. The turbine disk-rotor-support system is composed of turbine disk, rotating shaft, main bearing and other structures. It is the core component of an aero-engine. It has been working under high-speed, high-temperature, and high-load conditions for a long time. The structure is complex and vibration failures often occur, but At present, the failure mechanism of the aeroengine turbine disk-rotor-support system is not yet clear. Therefore, how to explain the failure mechanism from the perspective of the positive problem by establishi...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F30/17G06F30/23G06F119/14
Inventor 曹宏瑞苏帅鸣付洋乔百杰陈雪峰
Owner XI AN JIAOTONG UNIV
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