摘要
论文发展了一种预测航空燃气涡轮发动机压缩系统稳定工作边界的数学物理模型。其中压缩系统流动过程的动态模型采用基于平行压气机理论的准－维时间相关模型方程；叶片排对流动过程的影响则应用“激盘－滞后－容积”模型；压缩系统稳定性模型则采用了对整个压缩系统统一判别的方式。计算过程与发动机非设计性能计算相关联，使得压缩系统稳定性分析在真实的发动机运行环境（调节规律）下进行。在均匀进气条件下应用这种方法，对一台九级压气机的涡轮喷气发动机和一台三级低压风扇、五级高压压气机的低涵道比、混合排气、带加力的涡轮风扇发动机在均匀进气和畸变进气条件下的稳定工作边界，分别进行了数值模拟和分析。结果表明，发展的数学物理模型和计算机软件系统可以正确的反映发动机压缩系统的工作状况，用它判别发动机不稳定工作点的重复性和灵敏度都比较好。
A new model was presented for the prediction of aerodynamic stability limit of a compression system in turbine engine. A quasi one - dimensional, time dependent compression system model based on the parallel compressor theory was used to model the dynamic flow in compressor and the actuator- lag- volume model was adopted to model the stage of compressor. A united method was used to identify the stability of compression system instead of the identification of each segment compressor. The identification of stability of compression system was conducted under the condition when compressors run in engine. Numerical results show that the model presented in this paper is reasonable and reliable. A good consistency was found between prediction and test results from the compressor of a turbojet. The repetition and sensitivity of prediction results were good.
出处
《燃气涡轮试验与研究》
2001年第2期19-25,共7页
Gas Turbine Experiment and Research
