Aero-engine body vibration characteristic analysis method

A technology of aero-engine and vibration characteristics, applied in the direction of internal combustion engine testing, etc., can solve the problems of less joint research on the characteristics of rotating and static systems, weak engineering guidance, and poor consistency.

Active Publication Date: 2013-12-25
SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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Problems solved by technology

[0002] At present, the research on the vibration characteristics of the whole engine is mainly limited to the independent characteristic analysis of the rotor system, and the results obtained are not consistent with the actual working conditions of the engine. There are relatively few joint studies on the characteristics of the rotor and stator systems, and the guidance for engineering is not strong.

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Embodiment

[0025] This embodiment provides a method for analyzing the vibration characteristics of a complete aircraft engine, which is characterized in that: the complete engine system is isolated into a rotor system and a stator system, the two are coupled through a fulcrum system, and the dynamic characteristics of the rotor and stator systems are used co-simulation;

[0026] Firstly, the mechanical analysis of the whole engine system is carried out. The rotor system is the vibration source, and the stator system is the response body. The vibration energy of the rotor is transmitted to the stator system through the fulcrum in the form of support reaction force, and the response of the stator system can reflect the vibration characteristics of the whole machine. Divide a complex and almost unanalyzable huge system into analyzable subsystems, and organically combine each system through dynamic characteristic co-simulation, truly reflect the actual state of the whole machine, and realize ...

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Abstract

The invention discloses an aero-engine body vibration characteristic analysis method. An engine body system is separated into a rotor system and a stator system, the rotor system and the stator are coupled through a fulcrum system and are simulated jointly through dynamic characteristics of the rotor system and the stator system; the engine body system is separated into the two study objects, i.e., a rotor bearing system and a stator bearing system, and then vibration response and dynamic bearing reaction of the rotor bearing system are simulated and analyzed through a finite element analysis platform under the action of unbalanced exciting force and rub-impact force to acquire excitory input of the stator system; at last, the acquired dynamic bearing reaction and the rub-impact force are loaded on the stator bearing system, and the vibration response characteristics of the stator bearing system is simulated and analyzed to acquire engine body vibration characteristics. The aero-engine body vibration characteristic analysis method has the advantages of reducing hidden fault danger in the design of aero-engines and providing decision bases and technical support for engine vibration faults.

Description

technical field [0001] The invention relates to the field of vibration analysis of an aero-engine complete machine, in particular to a method for analyzing the vibration characteristics of an aero-engine complete machine. Background technique [0002] At present, the research on the vibration characteristics of the whole engine is mainly limited to the independent characteristic analysis of the rotor system. The results obtained are not consistent with the actual working conditions of the engine. There are relatively few joint studies on the characteristics of the rotor and stator systems, and the guidance for engineering is not strong. [0003] With the increasing urgency of the need to control the vibration faults of aero-engines, the accuracy, authenticity and comprehensiveness of the analysis results are increasingly demanding, and it is urgent to combine the dynamic characteristics of the full three-dimensional rotor-stator for the complete engine system. Simulation ana...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M15/12
Inventor 陈勇黄猛于丽君蒋晶博赵会琴
Owner SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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