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Flow stability analysis on low-speed compressor with swept rotor blades under radial inlet distortions
Aerospace Science and Technology ( IF 5.0 ) Pub Date : 2024-06-28 , DOI: 10.1016/j.ast.2024.109362 Dakun Sun , Hengyi Zhu , Dengke Xu , Haoyu Ni , Xiaofeng Sun
Aerospace Science and Technology ( IF 5.0 ) Pub Date : 2024-06-28 , DOI: 10.1016/j.ast.2024.109362 Dakun Sun , Hengyi Zhu , Dengke Xu , Haoyu Ni , Xiaofeng Sun
Flow stability enhancement for axial flow compressors under radially distorted inlet conditions through rotor sweep design is an important issue for designers. To investigate the couped effect of rotor swept and radial inlet distortion on flow stability, steady numerical simulations, theoretical model predictions, and experimental validations were conducted for a low-speed, single-stage axial compressor (TA36) under various intensities of tip total pressure distorted inlet conditions with different swept rotor configurations. The steady pressure rise significantly decreases as the intensity of the distortion increases, whereas the rotor sweep has little effect on the pressure rise characteristic. The maximum error via model prediction is 1.25 %, while for steady numerical calculation, it is 3.89 %. Higher intensities of distortion lead to worse flow stability. Under radially distorted inlet conditions, forward sweep enhances flow stability whereas backward sweep further worsens it. What's more, quantitative analysis shows that the stability enhancement of forward sweep cannot fully counteract the adverse impact of radial distortion on flow stability. Elevated rotor tip loading was identified as the primary cause of instability under tip total pressure distorted inlet conditions. Forward sweep can slightly reduce this loading, whereas backward sweep has the opposite effect. Furthermore, the impact of rotor sweep on rotor tip loading intensifies with increasing distortion intensity. Unsteady flow field analysis was conducted. Which shows that radial distortion and blade sweep both affect flow stability by altering the intensity of tip leakage flow.
中文翻译:
径向入口畸变下扫掠转子叶片低速压气机流动稳定性分析
通过转子扫掠设计来增强轴流压缩机在径向扭曲入口条件下的流动稳定性对于设计人员来说是一个重要问题。为了研究转子扫掠和径向入口变形对流动稳定性的耦合影响,对不同叶尖总压强度下的低速单级轴流压缩机 (TA36) 进行了稳态数值模拟、理论模型预测和实验验证不同扫频转子配置的扭曲入口条件。随着畸变强度的增加,稳定压力上升显着降低,而转子扫频对压力上升特性影响很小。模型预测的最大误差为1.25%,而稳定数值计算的最大误差为3.89%。变形强度越高,流动稳定性越差。在径向扭曲的入口条件下,前扫可增强流动稳定性,而后扫则进一步恶化流动稳定性。而且,定量分析表明,前掠稳定性的增强并不能完全抵消径向畸变对流动稳定性的不利影响。转子尖端负载升高被认为是尖端总压扭曲入口条件下不稳定的主要原因。向前扫掠可以稍微减少这种负载,而向后扫掠则具有相反的效果。此外,转子扫掠对转子尖端负载的影响随着畸变强度的增加而加剧。进行了非定常流场分析。这表明径向变形和叶片扫掠都通过改变叶尖泄漏流的强度来影响流动稳定性。
更新日期:2024-06-28
中文翻译:
径向入口畸变下扫掠转子叶片低速压气机流动稳定性分析
通过转子扫掠设计来增强轴流压缩机在径向扭曲入口条件下的流动稳定性对于设计人员来说是一个重要问题。为了研究转子扫掠和径向入口变形对流动稳定性的耦合影响,对不同叶尖总压强度下的低速单级轴流压缩机 (TA36) 进行了稳态数值模拟、理论模型预测和实验验证不同扫频转子配置的扭曲入口条件。随着畸变强度的增加,稳定压力上升显着降低,而转子扫频对压力上升特性影响很小。模型预测的最大误差为1.25%,而稳定数值计算的最大误差为3.89%。变形强度越高,流动稳定性越差。在径向扭曲的入口条件下,前扫可增强流动稳定性,而后扫则进一步恶化流动稳定性。而且,定量分析表明,前掠稳定性的增强并不能完全抵消径向畸变对流动稳定性的不利影响。转子尖端负载升高被认为是尖端总压扭曲入口条件下不稳定的主要原因。向前扫掠可以稍微减少这种负载,而向后扫掠则具有相反的效果。此外,转子扫掠对转子尖端负载的影响随着畸变强度的增加而加剧。进行了非定常流场分析。这表明径向变形和叶片扫掠都通过改变叶尖泄漏流的强度来影响流动稳定性。