| Computational Investigation of Blade Slotting on a High-Load Low-Pressure Turbine Profile at Various Reynolds Numbers：Part Ⅱ——Optimization of Slotting Position |
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| 作者姓名： | Qiang Du Junqiang Zhu Min Zhou Wei Li |
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| 作者单位： | [1]Institute of Engineering Thermophysics, Chinese Academy of Sciences, Beijing 100190, China [2]Graduate School of Chinese Academy of Sciences, Beijing, 100190, China [3]Key Laboratory of Advanced Energy and Power, Chinese Academy of Sciences, （Institute of Engineering Thermophysics）, Beijing 100190, China [4]Beijing Aeronautical Technology Research Center, Beijing, 100076, China |
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| 基金项目： | provided by the Supercomputing Center of Chinese Academy of Sciences and the sponsorship of National Natural Science Foundation of China |
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| 摘 要： |
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| 关 键 词： | 位置优化 计算结果 低压涡轮 高雷诺数 开槽 叶片表面 高负荷 气动载荷 |
| 收稿时间： | 28 February 2009 |
Computational investigation of blade slotting on a high-load low-pressure turbine profile at various reynolds numbers: Part II—Optimization of slotting position |
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| Qiang Du,Junqiang Zhu,Min Zhou,Wei Li.Computational investigation of blade slotting on a high-load low-pressure turbine profile at various reynolds numbers: Part II—Optimization of slotting position[J].Journal of Thermal Science,2011,20(1):21-25. |
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| Authors: | Qiang Du Junqiang Zhu Min Zhou Wei Li |
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| Affiliation: | (1) Department of Mechanical Engineering, The Hong Kong Polytechnic University, Kowloon, Hong Kong;(2) Department of Building Services Engineering, The Hong Kong Polytechnic University, Kowloon, Hong Kong;(3) School of Aeronautical Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing, China;(4) College of Engineering, Peking University, Beijing, China |
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| Abstract: | Boundary layer separation and reattachment is often an unavoidable feature of low pressure (LP) turbine, one of the main causes
of this phenomenon is the high altitude low Reynolds number experienced by the modern LP turbine stage in aero-engine. Although
an excellent turbine airfoil design can avoid flow separation on certain extent, but within flight envelope, LP turbine’s
characteristic Reynolds number may varied greatly, so it will be still under the risk of the presence of separation bubble.
In this two parts paper a new concept of slotted-blade was raised to testify the gain of the blade slotting. A high aerodynamic
loading LP turbine blade IET-LPTA was under investigated with different Reynolds number. Computational results reveal that
the blade slotting could be a way of choice to suppress separation bubble and reduce profile loss under the condition of low
Reynolds number, although its position and geometry need to be further investigated. |
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| Keywords: | Blade slotting Optimization Outlet angle Inlet position |
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