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以单级跨声轴流压气机NASA Stage35为研究对象,根据影响转子和静子通道流动的主要物理现象分别设计了多种引气方案.通过数值模拟比较分析引气与不引气状态下压气机的详细流场,结合实验测量结果,研究转子机匣端壁引气位置以及静子机匣端壁引气量对压气机性能及流场的影响.结果表明:转子机匣端壁引气能够有效控制间隙泄漏流的发展,减小叶尖损失,提升压气机性能.不同的引气槽结构和轴向位置对间隙流动的影响机理不相同;静子机匣端壁引气能够有效减小静子叶排损失,提升压气机效率.
Based on the single-stage transonic axial-flow compressor NASA Stage35, a variety of air-entraining schemes are designed according to the main physical phenomena that affect the flow of rotor and stator channels, respectively. Comparing the air-entraining and non- The experimental results show that the performance of the compressor and its flow field are influenced by the location of the bleed air at the end wall of the rotor casing and the amount of bleed air at the end wall of the stator casing.The results show that the air entrainment at the end wall of the rotor casing can be effectively controlled The development of interstitial leakage flow reduces the tip loss and enhances the performance of the compressor.Different structure and axial position of the bleed air groove have different influence mechanism on the flow of the gap.It is effective to reduce the stator vane row Loss, improve compressor efficiency.