Effects of Squealer Winglet on the Aerodynamic and Heat Transfer Performances of Turbine Rotor Blade Tip

被引：0
|
作者：
Jiang S. [1 ]
Li Z. [1 ]
Li J. [1 ]
机构：
[1] School of Energy and Power Engineering, Xi'an Jiaotong University, Xi'an
来源：
Hsi-An Chiao Tung Ta Hsueh/Journal of Xi'an Jiaotong University | 2019年 / 53卷 / 09期
关键词：
Aerodynamic performance; Numerical simulation; Squealer tip; Squealer winglet structure; Turbine rotor blade;
D O I：
10.7652/xjtuxb201909002
中图分类号：
学科分类号：
摘要：
Effects of squealer winglet structure on the heat transfer characteristics and aerodynamic performance of turbine rotor blade tip are numerically investigated using Reynolds-averaged Navier-Stokes (RANS) equation and k-ω turbulence model. Numerical results of the heat transfer coefficients distribution at rotor blade tip agree well with the experimental data and the reliabilty of this numerical method is validated. The numerical results show that the average heat transfer coefficients of rotor blade tip with squealer winglet structure on the pressure side or suction side, as well as on both pressure and suction sides, are decreased by 12.2%, 17.1% and 19.8%, respectively, in comparison with those of traditional squealer tip. Squealer winglet structure on the pressure and suction sides of the rotor blade tip can decrease the tip leakage flow and weaken the influence of corner and scraping vortexes near the pressure side. This flow behavior also decreases the heat transfer coefficient of rotor blade tip. In addition, the total pressure loss coefficients of rotor blade are increased by 8.5% when pressure side has squealer winglet structure, and decreased by 8.5% and 2.5% when suction side has squealer winglet structure and both sides have squealer winglet structures, respectively in comparison with traditional squealer tip profile. The suction side with squealer winglet structure can effectively decrease the heat transfer coefficient and aerodynamic loss. Finally, a tradeoff in the aerothermal performance of the suction side with squealer winglet structure at the rotor blade squealer tip is obtained. © 2019, Editorial Office of Journal of Xi'an Jiaotong University. All right reserved.
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页码：7 / 14and41
页数：1434
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