航天推进技术研究院主办
[1]严俊峰,逯婉若.冲击式涡轮内部流动数值研究[J].火箭推进,2009,35(01):31-35.
Yah Junfeng,Lu Wanruo.Numerical analysis of inner flow field for an impulse turbine[J].Journal of Rocket Propulsion,2009,35(01):31-35.
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Yah Junfeng,Lu Wanruo.Numerical analysis of inner flow field for an impulse turbine[J].Journal of Rocket Propulsion,2009,35(01):31-35.
冲击式涡轮内部流动数值研究
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
35
期数:
2009年01期
页码:
31-35
栏目:
研究与设计
出版日期:
2009-02-27
- Title:
- Numerical analysis of inner flow field for an impulse turbine
- Keywords:
- turbl’ne; numencal simulation; efficiency
- 分类号:
- V434.21 1
- 文献标志码:
- A
- 摘要:
- 利用商业计算流体力学软件Numeca对某冲击式涡轮在不同工况下的内流场进 行了定常流动数值模拟，分析了涡轮的气动参数、流量及效率等的变化规律。分析表明．冲 击式涡轮内部流场非常复杂，涡轮静子出口马赫数较高，相应的激波损失较大．从而涡轮转 子的激波损失也较大，造成气流在靠近尾缘部分分离严重，这是冲击式涡轮追求低出口速度 低反力度造成的。计算表明，模拟计算结果与试验结果较为吻合。
- Abstract:
- The numerical analysis of the inner flow field using Numeca is presented at the different work points for an impulse turbine．The changes of the aerodynamic parameters，the mass flow and the isentropic efficiency have been investigated in detail．It can be concluded that the flow field in the impulse turbine is very complicated．High Mach number in turbine stator outflow results in a bigger loss of shocks．Airflow separation is serious on the trailing edge of turbine rotor，which is caused by smaller outlet velocity of impulse turbine in low reaction degree conditions．The results show that the numerical analysis data are in agreement with the experimental data．
参考文献/References:
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械学术会议．2007．
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靠性的影响[J]．火箭推进，2007，33(1)：32—35．
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备注/Memo
收稿日期：2008—08一01；修回日期：2008—09—03。 作者简介：严俊峰(1980--)，男，工程师，研究领域为涡轮泵设计。
更新日期/Last Update:
1900-01-01