The invention belongs to the technical field of turboshaft engines, and provides a control method and system for improving the temperature distortion resistance of a turboshaft engine, and the method comprises the steps: judging whether the air inlet temperature of any engine is distorted and exceeds the limit or not; if the distortion exceeds the limit, adjusting the angle of an inlet guide vane of the engine and an acceleration rate limit value; and after the engine inlet guide vane is adjusted, if no distortion exceeds the limit within the target duration, the angle of the engine inlet guide vane and the acceleration rate limit value are adjusted back. According to the control method for improving the temperature distortion resistance of the turboshaft engine, the analysis process for judging whether the air inlet temperature of the engine is distorted and exceeds the limit or not is elaborated, different treatment processes are provided according to the number of the engines and the number of the temperature sensors, and whether the air inlet temperature of the engine exceeds the limit or not is helped to be judged; and then the acceleration rate and the engine inlet guide vane angle are adjusted according to the over-limit condition, the temperature distortion resistance of the engine is improved, engine surge is avoided, and the flight quality and safety are improved.

    本发明属于涡轴发动机技术领域,提供了一种提高涡轴发动机抗温度畸变能力的控制方法及系统,其中方法包括:判断任意一台发动机的进气温度是否畸变超限;若畸变超限,则调整发动机进口导叶的角度和加速率限制值;发动机进口导叶调整后,若在目标时长内未畸变超限,则将发动机进口导叶的角度和加速率限制值回调。本发明提出的提高涡轴发动机抗温度畸变能力的控制方法阐述了判断发动机进气温度是否畸变超限时的分析过程,其根据发动机数量和温度传感器的数量提出了不同的处理过程,帮助判断发动机的进气温度是否超限,然后根据超限情况调整加速率及发动机进口导叶角度,提高发动机抗温度畸变的能力,避免发动机喘振,提高飞行品质和安全性。


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    Title :

    Control method and system for improving temperature distortion resistance of turboshaft engine


    Additional title:

    一种提高涡轴发动机抗温度畸变能力的控制方法及系统


    Contributors:
    DUAN HUI (author) / HUANG KAIMING (author) / CHEN FEIYANG (author) / LI WEI (author) / ZHOU YONG (author) / YANG FANG (author) / YI SHENG (author)

    Publication date :

    2024-07-12


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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