基于差异演化算法和残差修正的涡轮增压机组防喘振控制

某型船用涡轮增压机组在低负荷运行时压气机容易发生喘振的问题。在涡轮增压机组喘振机理分析的基础上，采用差异演化算法辨识机组的理论喘振边界线，并利用机组出厂试验数据和理论计算结果的残差进行修正，避免采用经验值或理想状态下的实验数据作为辨识依据所造成的误差。在辨识得到的喘振边界线和已有涡轮增压机组模型的基础上，研究某型船用增压锅炉涡轮增压机组在低负荷运行时的喘振特性，并通过仿真实验得到压气机转速、增压比、空气流量与防止喘振的旁通阀最小开度与空气旁通流量之间的关系。结果表明：当压气机转速低于额定转速的8.35%时，必须紧急停机后重新启动；当转速高于额定转速的20.37%时，正常情况下不会出现喘振现象；当转速介于额定转速的8.35%~20.37%时，应保持对应的旁通挡板安全开度。

Active surge control of marine turbocharged units based on differential evolutionary modeling with residual correction

A certain type of turbocharged unit can easily surge when it is operated under a low load. This study is based on an analysis of the mechanism of turbocharged unit surge, identifying the surge boundary parameter using Differential Evolutionary(DE) algorithm, and using the residuals of actual test data and theoretical calculation results to correct errors, which avoids the deviation caused by using the experiential value or experimental data under an ideal state as the identification. Studying the characteristics of turbocharged unit surge under low load is based on the obtained surge boundary curve and the existing turbo charging model. The relationships between the compressor rotor speed, pressure ratio, air flux, minimal opening and bypass baffle air flux were obtained through simulation experiments. The results show that the unit must be restarted when the rotor speed of the compressor is under 8.35% of the rated speed; the surge will disappear when the rotor speed of the compressor exceeds 20.37% of the rated speed, and the safe opening of the bypass baffle that corresponds to the rotor speed of the compressor should be kept up when the rotor speed is between 8.35% and 20.37% of the rated speed.