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An Investigation of Using Tip Leakage Interrupter and Blade Slit to Mitigate Aerodynamic Losses in Axial Turbine Stage

机译：使用尖端泄漏断路器和刀片切口的研究，以减轻轴向汽轮机阶段的气动损失

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作者
?Andichamy, Veerandra Chakkaravarthy;
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作者单位

The Pennsylvania State University;

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授予单位 The Pennsylvania State University;
学科
学位 Ph.D.
年度 2019
页码 218 p.
总页数 218
原文格式 PDF
正文语种 eng
中图分类
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1. Aerodynamic impact of hub and shroud leakage flow on an axial turbine stage [J] . Liu Huoxing, An Yuge, Zou Zhengping Proceedings of the Institution of Mechanical Engineers, Part C. Journal of mechanical engineering science . 2016,第14期

机译：轮毂和护罩泄漏流对轴向涡轮级的气动影响
2. Aerodynamics of Tip Leakage Flows Near Partial Squealer Rims in an Axial Flow Turbine Stage [J] . Cengiz Camci, Debashis Dey, Levent Kavurmacioglu Journal of turbomachinery . 2005,第1期

机译：轴流式水轮机阶段部分阻风门边缘附近的尖端泄漏流的空气动力学
3. Influence of blade lean together with blade clocking on the overall aerodynamic performance of a multi-stage turbine [J] . Zhu Yalu, Luo Jiaqi, Liu Feng Aerospace science and technology . 2018,第SEPa期

机译：叶片倾斜和叶片计时对多级涡轮机整体空气动力性能的影响
4. Investigation of the tip-leakage losses in turbine axial stages [C] . A Szymański, S Dykas, W Wróblewski, Fluid Mechanics Conference . 2014

机译：汽轮机轴向阶段尖端泄漏损耗的研究
5. Numerical investigation of the unsteady aerodynamics of blade tip leakage flow inside gas turbine engines. [D] . Phutthavong, Patricia. 2006

机译：燃气轮机内部叶片尖端泄漏流动非定常空气动力学的数值研究。
6. Influence of Reynolds Number on Multi-Objective Aerodynamic Design of a Wind Turbine Blade [O] . Mingwei Ge, Le Fang, De Tian -1

机译：雷诺数对风力涡轮机叶片多目标空气动力学设计的影响
7. Aerodynamic performance of endwall contoured turbine blades considering leakage flow interaction [O] . Zimmermann Tobias Winfried 2017

机译：考虑泄漏流相互作用的端壁轮廓涡轮叶片的空气动力学性能
8. Computer program describing turbine aerodynamic requirements, approximate external blade geometries, and coolant flow requirements for a two stage axial flow turbine [R] . Evans, D. G., Furgalus, K. A., Vanco, M. R. 1971

机译：描述涡轮空气动力学要求，近似外部叶片几何形状和两级轴流式涡轮机的冷却剂流量要求的计算机程序

An Investigation of Using Tip Leakage Interrupter and Blade Slit to Mitigate Aerodynamic Losses in Axial Turbine Stage

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