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Equivalent modeling method for complex rotor system of aero-engine

An aero-engine and equivalent modeling technology, applied in the field of effective modeling, can solve problems such as low calculation accuracy and low calculation efficiency of complex rotor systems, and achieve the effects of improving calculation accuracy, overcoming low calculation efficiency, and improving calculation efficiency

Active Publication Date: 2016-07-06
CHINA AVIATION POWER MACHINE INST
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Problems solved by technology

[0005] The invention provides an equivalent modeling method of a complex rotor system of an aero-engine to solve the technical problems of low calculation efficiency and low calculation accuracy of the complex rotor system

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  • Equivalent modeling method for complex rotor system of aero-engine
  • Equivalent modeling method for complex rotor system of aero-engine
  • Equivalent modeling method for complex rotor system of aero-engine

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Embodiment Construction

[0047] It should be noted that, in the case of no conflict, the embodiments in the present application and the features in the embodiments can be combined with each other. The present invention will be described in detail below with reference to the accompanying drawings and examples.

[0048] refer to figure 1 , the preferred embodiment of the present invention provides a kind of equivalent modeling method of complex rotor system of aero-engine, comprises steps:

[0049] Step S100 , performing static equivalent analysis on the solid rotor structure of the complex rotor system to obtain the geometric dimensions of the equivalent model.

[0050] Perform static equivalent analysis on the solid rotor structure of the complex rotor system to obtain the geometric dimensions of the equivalent model. The geometric dimensions of the equivalent model can be the equivalent outer diameter of the rotor shaft or the equivalent inner diameter of the rotor shaft. This will not list them on...

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Abstract

The invention discloses an equivalent modeling method for a complex rotor system of an aero-engine. The method comprises the steps of obtaining a geometric size of an equivalent model by performing static equivalent analysis on a solid rotor structure of the complex rotor system; according to the geometric size of the equivalent model, re-correcting material parameters of the solid rotor structure, and determining a rotor structure after equivalent modeling; and performing power verification on the determined rotor structure after equivalent modeling. According to the method, a static analysis result and a power analysis result of the rotor system are effectively combined, so that the calculation precision of the complex rotor system is improved; and the problem of low calculation efficiency of a three-dimensional finite element unit is solved, so that the calculation efficiency of nonlinear dynamic response of rotor dynamics can be greatly improved.

Description

technical field [0001] The invention relates to the field of rotor modeling of an engine, in particular to an equivalent modeling method of a complex rotor system of an aeroengine. Background technique [0002] Rotating machinery is widely used in mechanical devices including gas turbines, industrial compressors, electric motors and aircraft engines. Because it plays a very important role in the field of aviation, the study of its dynamic characteristics has also formed a special discipline - rotor dynamics. Rotordynamics is the study of all dynamic characteristics related to rotating machinery rotors and their components and structures, including dynamic response, vibration, strength, fatigue, stability, reliability, fault diagnosis and control. [0003] The research model of rotor dynamics. In 1895, Foppl proposed the initial and simplest Jeffcott rotor model, which is composed of a massless shaft with rigid supports at both ends and a disc in the middle. With the improv...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
CPCG06F30/23
Inventor 吴春来蔡显新陈亚农
Owner CHINA AVIATION POWER MACHINE INST
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