The invention relates to the technical field of aero-engine parts, in particular to a rigidity-variable aero-engine support, a temperature control system and a design method. In order to solve the problems that the inherent frequency of an existing aero-engine support cannot be adjusted, and the resonance frequency cannot be effectively avoided when the resonance risk occurs, the invention provides the aero-engine support with the variable rigidity and the design method of the aero-engine support with the variable rigidity and the design method of the aero-engine support. The temperature of the shape memory alloy supporting column serving as a variable stiffness mechanism can be monitored in real time through the digital display thermometer, the energization time and the current intensity of the copper core enameled wire are adjusted in real time through the programmable power source in cooperation with the resistance box according to a displacement feedback signal of an accessory, active vibration reduction of an aero-engine accessory system is achieved, and the service life of the aero-engine accessory system is prolonged. In the conversion process, the rigidity of the aero-engine support is manually and actively regulated and controlled, the inherent frequency of the aero-engine support can be changed when the resonance risk occurs, and a resonance area is effectively avoided.

    本发明涉及航空发动机部件技术领域,具体涉及刚度可变的航空发动机支架、温度控制系统及设计方法。为了解决现有的航空发动机支架固有频率无法调节,发生共振风险时无法有效避开共振频率的问题,提出一种刚度可变的航空发动机支架及其设计方法,给变刚度机构上设置的铜芯漆包线通电的方式提高其环境温度,使得作为变刚度机构的形状记忆合金支柱上的温度可通过数显温度计进行实时监测,并根据附件的位移反馈信号,通过可编程电源配合电阻箱对铜芯漆包线通电时间和电流强度进行实时调节,实现了航空发动机附件系统的主动减振,此转变过程实现了人为主动调控航空发动机支架的刚度,当发生共振风险时可改变其固有频率,有效避开共振区。


    Zugriff

    Download


    Exportieren, teilen und zitieren



    Titel :

    Rigidity-variable aero-engine support, temperature control system and design method thereof


    Weitere Titelangaben:

    刚度可变的航空发动机支架、温度控制系统及其设计方法


    Beteiligte:
    WANG ZIYAO (Autor:in) / ZHANG YICHI (Autor:in) / LU KUAN (Autor:in) / YANG YANG (Autor:in) / JIN YULIN (Autor:in) / ZHAO XIANFENG (Autor:in) / ZHANG HAOPENG (Autor:in) / ZHANG KANGYU (Autor:in) / GUO DONG (Autor:in) / CHEN JIN (Autor:in)

    Erscheinungsdatum :

    2023-09-22


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F16F SPRINGS , Federn / G05D SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES , Systeme zum Steuern oder Regeln nichtelektrischer veränderlicher Größen / G06F ELECTRIC DIGITAL DATA PROCESSING , Elektrische digitale Datenverarbeitung



    Aero engine design

    Engineering Index Backfile | 1916


    Aero engine design

    Wilkinson, G.S. | Engineering Index Backfile | 1934


    Aero Engine Design

    Ford, Terry | Emerald Group Publishing | 1992


    Active control type variable-rigidity anti-side-rolling torsion bar device and variable-rigidity method thereof

    LI PENG / ZOU MINJIA / LIU WENSONG et al. | Europäisches Patentamt | 2020

    Freier Zugriff

    Maintenance support member for aero-engine

    HAN XING | Europäisches Patentamt | 2021

    Freier Zugriff