| 涡轮非定常流数值计算方法研究 |
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| 引用本文： | 葛宁.涡轮非定常流数值计算方法研究[J].航空动力学报,2009,24(5):1066-1070. |
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| 作者姓名： | 葛宁 |
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| 作者单位： | 南京航空航天大学 能源与动力学院, 南京 210016 |
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| 摘 要： | 在实际叶片排几何模型不变的条件下,采用交接面周期性处理方法可大大缩小非定常流计算域,减小计算量,但该处理方法会给非定常流计算带来一些近似,通过某跨声速涡轮级三维粘流数值计算,分析和评估计算方法,结论是该方法不改变时间平均下的稳态性能参数,而且可用于多级涡轮非定常流计算.
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| 关 键 词： | E3高压涡轮级 非定常流计算 交接面缩放 多级涡轮 性能参数 |
| 收稿时间： | 2008/5/14 0:00:00 |
| 修稿时间： | 2008/11/8 0:00:00 |
Evaluation of a numerical calculation method for unsteady flow in turbomachinery |
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| GE Ning.Evaluation of a numerical calculation method for unsteady flow in turbomachinery[J].Journal of Aerospace Power,2009,24(5):1066-1070. |
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| Authors: | GE Ning |
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| Institution: | College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China |
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| Abstract: | The real blade-to-blade passage geometry can be computed owing to approximate treatment of the flow continuity condition on periodic boundaries.This technique is specifically intended to reduce the computational domain.The boundary treatment induces some approximate computation of the unsteady flow phenomena.These were analyzed in the cases of the E3 high-pressure turbine in which the viscous flow was computed.The main conclusion is that,this approach doesn't affect the time average performance parameters a... |
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| Keywords: | E3 high-pressure turbine unsteady flow simulation interface contraction/dilatation multi-stage turbines performance parameters |
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