叶尖间隙高度对某高压涡轮级损失分布的影响

王大磊; 朴英

叶尖间隙高度对某高压涡轮级损失分布的影响

王大磊,
朴英

清华大学航天航空学院,北京 100084

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出版历程
- 收稿日期: 2011-01-13
- 修回日期: 2011-06-29
- 刊出日期: 2012-01-28

Influence of tip clearance size on flow losses of a transonic high pressure turbine stage

School of Aerospace, Tsinghua University, Beijing 100084, China

摘要

摘要: 利用三维湍流数值模拟方法模拟某一级跨声速高压涡轮流场,研究转子叶片叶尖间隙高度对涡轮性能及二次流动损失分布的影响.研究结果表明:转子叶尖间隙高度对涡轮性能影响明显,随着间隙高度的增加涡轮效率明显降低,但效率的降低速度与间隙高度并非简单线性关系,间隙高度增加1%相对叶高,涡轮性能最快下降1.8%.分析表明:涡轮转子间隙高度变化主要影响转子叶栅通道上部流动并对通道内的损失分布产生影响.其中损失最严重的区域为转子通道中部至叶片尾缘处;尾缘后的损失则对间隙的高度最敏感,随着间隙高度的增加,叶片尾缘后损失明显增加.
- 航空发动机 /
- 高压涡轮级 /
- 叶尖间隙 /
- 流动损失 /
- 数值模拟
Abstract: The influence of the tip clearance height of turbine rotor blades on the aerodynamic performance and secondary flow losses of an axial turbine stage were investigated by numerical simulation and different tip clearance heights were taken into account.Results show that the efficiency of the turbine stage would decrease markedly due to the increase of the tip clearance height.The efficiency would decrease 1.8% as the tip clearance height increased 1% of blade relative height.Analyses of the rotor flow field indicated that as the height if tip clearance increased,the distribution of flow losses changed in the upper passage of the rotor.The most losses were induced in the region between the middle of the rotor blade and the trailing edge,while secondary flow losses increased most behind the trailing edge.Mixing losses were the main factors which led to the efficiency decreased as the height of tip clearance increased.
- aero-engine /
- high pressure turbine stage /
- tip clearance /
- flow loss /
- numerical simulation

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参考文献(18)

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