上游尾迹与涡轮叶栅通道涡相互作用研究

綦蕾; 郑贇; 邹正平; 刘火星; 李维; 周颖; 许如琦

上游尾迹与涡轮叶栅通道涡相互作用研究

1.
北京航空航天大学, 能源与动力工程学院, 航空发动机气动热力重点实验室, 航空发动机数值仿真研究中心, 北京 100083
2.
中国航空动力机械研究所, 株洲 412002

基金项目: 国家自然科学基金项目(50776003);国防基础科研项目;北京航空航天大学蓝天新星计划资助项目

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出版历程
- 收稿日期: 2007-04-20
- 修回日期: 2007-08-27
- 刊出日期: 2008-05-28

Upstream wake-passage vortex interaction in turbine cascade

1.
Aeroengine Numerical Simulation Research Center, National Key Laboratory on Aero-Engines, School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100083, China
2.
China Aviation Powerplant Research Institute, Zhuzhou 412002, China

摘要

摘要: 采用三维粘性非定常数值模拟方法研究了上游尾迹与涡轮叶栅通道涡的相互作用,对定常、非定常时均以及瞬时时刻流动机理进行了分析.结果表明:上游尾迹的非定常作用一方面增强了叶栅通道涡的径向涡,使得流动损失增大;另一方面能够一定程度上抑制通道涡中流向涡的发展,对控制损失起到正面作用,端区的综合非定常效应取决于两者之间的平衡.在本文计算条件下,上述两方面综合影响使得通道涡的非定常损失增大.
- 航空、航天推进系统 /
- 通道涡 /
- 上游尾迹 /
- 非定常相互作用 /
- 涡轮叶栅
Abstract: The internal flow of turbomachinery is intrinsically unsteady,so investigating the unsteady interactions in turbine endwall region is meaningful for improving the performance of low aspect/high loading turbine.In this paper,the upstream wake-passage vortex interactions in turbine cascade were simulated by a 3-Dunsteady viscous solver,and the flow mechanisms were analyzed.Numerical results indicate that periodic upstream wakes can enhance the radial vorticity of passage vortex,which increases losses.On the other hand,upstream wakes can suppress the streamwise vorticity development of passage vortex to some extent,which reduces losses.The combined unsteady effect in the endwall region depends on the balance of above two factors.At the calculation conditions of this paper,the unsteady losses finally increased.
- aerospace propulsion system /
- passage vortex /
- upstream wake /
- unsteady interaction /
- turbine cascade

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参考文献(12)

[1]	Pullan G,Denton J,Curtis E.Improving the performance of a turbine with low aspect ratio stators by aft-loading[R].ASME 2005-GT-68548.
[2]	Denton J D.Loss mechanisms in turbomachinery[R].ASME 93-GT-435.
[3]	石靖.高负荷高效率高温涡轮的研究与发展问题[C]∥中国航空学会21世纪航空动力发展研讨会论文集.北京:中国航空学会动力专业分会,2000:117-121.
[4]	季路成,周盛.转/静干扰效应纳入设计体系的途径探索[J].工程热物理学报,1999,20(5):580-583.JI Lucheng,ZHOU Sheng.Exploration of the rotor-stator interaction applying to design system[J].Journal of Engineering Thermophysics,1999,20(5):580-583.
[5]	Schlienger J,Kalfas A I,Abhari R S.Vortex-wake-blade interaction in a shrouded axial turbine[R].ASME 2004-GT-53915.
[6]	Graham P.Secondary flows and loss caused by blade row interaction in a turbine stage[R].ASME 2004-GT-53743.
[7]	马宏伟,蒋浩康,马艳红,等.涡轮叶栅端壁区非定常流场显示[J].工程热物理学报,2000,21(2):170-173.MA Hongwei,JIANG Haokang,MA Yanhong,et al.The unsteady flow visualization in turbine cascade endwall region[J].Journal of Engineering Thermophysics,2000,21(2):170-173.
[8]	邹正平,叶建,张永新,等,非定常流动对叶片表面负荷分布影响的数值模拟研究[J],燃气涡轮试验与研究,2006,19(1):21-26.ZOU Zhengping,YE Jian,ZHANG Yongxin,et al.Numerical simulation of unsteady flow effects on turbine blade loading distributions[J].Gas Turbine Experiment and Research,2006,19(1):21-26.
[9]	Miller R J,Moss R W,Ainsworth R W,et al.Time-resolved vane-rotor interaction in a high-pressure turbine stage[J].ASME Journal of Turbomachinery,2003,125(1):1-13.
[10]	Miller R J,Moss R W,Ainsworth R W,et al.The development of turbine exit flow in a swan-necked inter-stage diffuser[R].ASME 2003-GT-38174.
[11]	Borislav T,Sirakov,Choon S T.Effect of upstream unsteady flow conditions on rotor tip leakage flow[R].ASME 2002-GT-30358.
[12]	Cardamone P,Stadtmiiller P,Fottner L.Numerieal investigation of the wake-boundary layer interaction on a highly loaded LP turbine cascade blade[R].ASME 2002-GT-30367.