某型加力涡扇发动机变几何扩稳优化模拟

A Study of Enlarging Surge Margin and Optimization of Variable Geometry for Afterburning Turbofan Engines

本文基于级特性和级叠积模型 ,发展了涡扇发动机风扇压气机导叶、静叶调节扩大发动机稳定裕度的计算模型 ,并将其与某型加力涡扇发动机共同工作计算模型相结合 ,建立了低函道比加力涡扇发动机风扇和压气机变几何调节扩稳的模拟方法及相应的计算模拟程序 ,并对发动机变几何的调节方案进行了初步的优化分析 ,结果表明合理的发动机变几何调节可使发动机性能和稳定裕度获得最佳匹配。

A general model for predicting the thermodynamic performance of variable geometry axial compressors has been developed,based on stage-stacking model.The model is combined with the method,with which off-design operating points of gas turbine engines can be predicted.The simulation program is established for predicting variations in engine surge margins.An example on the use of the model and method is given to prove their validity.The optimization is obtained to predict the effects of combined variable geometry of fan inlet guide vane,mixer and nozzle area on the performances and surge margins of the engine.