Investigation on Film Cooling and Aerodynamic Performance of the Multi-Cavity Tip with Inclined Film Holes in a Linear Turbine Cascade

被引：0
|
作者：
Jia Z. [1 ]
Li F. [1 ]
Zhang W. [1 ]
Liu Z. [1 ]
Shi Y. [2 ]
Feng Z. [1 ]
机构：
[1] School of Energy and Power Engineering, Xi'an Jiaotong University, Xi'an
[2] China United Gas Turbine Technology Co., Ltd., Beijing
来源：
Hsi-An Chiao Tung Ta Hsueh/Journal of Xi'an Jiaotong University | 2023年 / 57卷 / 09期
关键词：
aerodynamic characteristics; film cooling; gas turbine; multi-cavity tip; pressure sensitive paint;
D O I：
10.7652/xjtuxb202309002
中图分类号：
学科分类号：
摘要：
In order to improve the film cooling effectiveness and reduce the aerodynamic loss of the gas turbine blade tips, an experiment was conducted to investigate the film cooling characteristics of the multi-cavity tips with inclined film holes, and the aerodynamic performance of these tips was numerically simulated. Firstly, the variation rule of the film cooling performance of four types of multi-cavity tips, of which the cavity number was one* two. three and four respectively, was measured under four blowing ratios (0. 5.1.0.1.5 and 2.01 by the pressure sensitive paint technique. Secondly, after the validation of turbulence models, the SST k-<o turbulence model, which showed the most excellent agreement with experimental results, was adopted to simulate the flow field structure and aerodynamic loss of the multi-cavity tips. The results show that the multi-cavity tips have better film cooling coverage on the front and middle parts of the tips as well as the rims: the installed ribs of the multi-cavity tips can prevent the coolant from flowing downstream and induce vortices behind the ribs to involve the coolant-leading to better film cooling effectiveness on the upstream and downstream parts of the ribs; compared with the conventional cavity tips-the aerodynamic loss of the multi-cavity tips are lower, of which the three-cavity tips performs the lowest loss coefficient and it is 9. V/i lower than that of the conventional cavity tip at most. © 2023 Xi'an Jiaotong University. All rights reserved.
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页码：10 / 21
页数：11
相关论文
共 28 条
  • [1] ZHENG Qun, Et al., Research progress On turbine blr-de tip aerodynamics and heat transfer technology for gas turbines [J], Acta Aeronautica et Astronautica Sinica, 3, 9, pp. 71-101, (2017)
  • [2] HAN jr. Film-cooling effectiveness on a gas turbine Wade tip using pressure-sensitive paint [J], Journal of Heat Transfer, 127, 5, pp. 521-530, (2005)
  • [3] AZAD G S., HAN J C, BOYLE R J., Heat transfer and flow on the squealer tip of a gas turbine blade [J], Journal of Turbomachinery, 122, 4, pp. 725-732, (2000)
  • [4] RANG D B., LEE S W., Effects of squealer rim height On heat/mass transfer on the floor of cavity squealer tip in a high turning turbine blade cascade [JJ. Inter-nation[J], Journal of Heat and Mass Transfer, (2016)
  • [5] SENEL C B., MARAL H., KAVURMACIOGLU L A., Et al., An aerothermal study of the influence of squealer width and height near a HP turbine hlade [J], International Journal of Heat and Mass Transfer-2018, 12, pp. 18-32
  • [6] LI Chenxi S, X1ANG Jiacheng, SONG Liming, Et al., An aerothermal analysis of the effects of tip gap height and cavity depth of a gas turbine blade [J], International Journal of Thermal Sciences, 158, (2020)
  • [7] SAKAOGLU S., KAHVECI H S., Effect of cavity depth on thermal performance of a cooled blade tip under rotation [J], International Journal of Heat and Mf.ss Transfer, 143, (2019)
  • [8] ZHANG Qiang, LU Shaopeng, Et al., Relative casing motion effect on sqi.iec.ler tip cooling performance at tight tip clearance [J OL_, Journal of Thermal Science and Engineering Applications, pp. 1-18, (2020)
  • [9] YANG Dianliang, FENG Zhenping, Effects of squealer tip on blade aerodynamic performance and tip heat transfer in gas turbine [_]], Journal of Xi'an Jiaotong University, 12, 7, pp. 83S-842, (2008)
  • [10] DU Kun-LI Jun, Numerical investigations on unsteady leakage flow and heat transfer characteristics of turbine blade with squealer tip, Journal of Propulsion Technology, pp. 551-558, (2017)
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