发动机压缩系统稳定工作边界的预测方法  

Prediction on of Stability Operating Limit in Aeroengines

作　　者：黄知涛[1] 胡正峰[1] 乔渭阳[1] 李文兰[1] 

机构地区：[1]西北工业大学航空动力与热力工程系,陕西西安710072

出　　处：《航空动力学报》2000年第1期51-54,共4页Journal of Aerospace Power

摘　　要：本文介绍一种模拟发动机(涡喷、涡扇)压缩系统气动稳定性的数值模型和数值方法,并给出3 个算例及其分析。它可用以预计部件台或双轴涡喷、涡扇发动机环境中风扇和高压压气机的稳定工作边界。发动机的主调节规律可以是nf = 常数或nh = 常数。初步结果表明,描述气动稳定性的数学模型和稳定性判别方法是可行的。级特性(级性能模型)对稳定性预算结果有重要影响,当缺乏级特性试验数据时,可以使用本文所述的级性能模型,用这个模型堆叠的部件总特性在中。A model for predicting aerodynamic stability of axial compressor in turbojet or turbofan engine is presented.The detailed numerical analyses for three examples for stability operating limits of 9-stage compressor,3-stage fan and 5-stage high-pressure compressor are given.It is shown that the compressor stability operating limit can be precisely predicted when control rule is n f =constant or n h =constant.It is also found that the numerical model and recognition criterion for aerodynamic stability in the axial compressor are feasible.The computed results are in good agreement with the experimental data obtained at medium and high rotating speeds.

关 键 词：气动稳定 涡扇发动机 压缩系统 稳定工作边界 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]