压力面侧小翼结构对凹槽叶顶冷却传热性能的影响

黄琰; 晏鑫; 何坤; 李军; 丰镇平

doi:10.7652/xjtuxb201707008

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压力面侧小翼结构对凹槽叶顶冷却传热性能的影响

更新时间：2025-07-09

- 压力面侧小翼结构对凹槽叶顶冷却传热性能的影响
- Effect of Pressure Side Winglet on Film Cooling and Heat Transfer Performance of Blade Squealer Tip
- 西安交通大学学报 2017年51卷第7期页码：51-56
- 作者机构：
  
  西安交通大学能源与动力工程学院,西安,710049
- 作者简介：
- 基金信息：
  
  : 2016-10-13。作者简介: 黄琰(1992—),女,硕士生;晏鑫(通信作者),男,副教授。基金项目: 国家自然科学基金资助项目(51306138)
- DOI：10.7652/xjtuxb201707008
  中图分类号： TK474.7
- 网络首发：2017-07-10，
  
  纸质出版：2017
- 稿件说明：
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黄琰, 晏鑫, 何坤, 等. 压力面侧小翼结构对凹槽叶顶冷却传热性能的影响[J]. 西安交通大学学报, 2017,51(7):51-56.

Effect of Pressure Side Winglet on Film Cooling and Heat Transfer Performance of Blade Squealer Tip[J]. 2017, 51(7): 51-56.
黄琰, 晏鑫, 何坤, 等. 压力面侧小翼结构对凹槽叶顶冷却传热性能的影响[J]. 西安交通大学学报, 2017,51(7):51-56. DOI： 10.7652/xjtuxb201707008.

Effect of Pressure Side Winglet on Film Cooling and Heat Transfer Performance of Blade Squealer Tip[J]. 2017, 51(7): 51-56. DOI： 10.7652/xjtuxb201707008.

摘要

采用数值计算方法对带压力侧小翼凹槽叶顶附近的流动、传热和冷却特性进行了研究

计算获得了无气膜孔、单排气膜孔和双排气膜孔3种孔分布条件下叶顶区域的流场结构、传热系数和气膜冷却有效度

并与常规凹槽叶顶和无压力侧肩壁凹槽叶顶的冷却传热性能进行了比较。结果表明:与常规和无压力侧肩壁凹槽叶顶相比

带压力侧小翼凹槽叶顶具有更优的气动、传热和冷却性能; 带压力侧小翼凹槽叶顶的总压损失与无压力侧肩壁凹槽叶顶的相近

比常规凹槽叶顶的低约10%; 在3种孔分布条件下

带压力侧小翼凹槽叶顶的平均传热系数均最小

平均气膜冷却有效度最大。气膜孔分布影响了带压力侧小翼凹槽叶顶冷却流的作用范围

带压力侧小翼凹槽叶顶中弧线处的冷却流覆盖了凹槽底部吸力面侧区域

小翼处的冷却流能较好地冷却小翼和凹槽底部压力面侧区域。该结果可为增强凹槽叶顶的冷却传热性能提供参考。

Abstract

Aerodynamic

heat transfer and film cooling performance on the squealer tip with pressure side winglet are numerically investigated. For three different cooling-hole arrangements

i. e. no film cooling hole

single hole-array located at the tip camber line

and two hole-arrays located at the tip camber line and pressure-side winglet

the flow structures

heat transfer and film cooling performance in the pressure-side winglet tip region are obtained. The predicted film cooling and heat transfer performance of the pressure-side winglet tip are also compared with the conventional squealer tip and squealer tip without pressure side rim configurations. The results show that compared with the other two tip configurations

the squealer tip with pressure side winglet is endowed with the superior performance of aerodynamic

heat transfer and film cooling effect in the blade tip region. The total pressure loss in the squealer tip with pressure side winglet gets close to that in squealer tip without pressure side rim

and is about 10% lower than that in the conventional squealer tip. For different cooling-hole arrangements

the average heat transfer coefficient on the squealer tip with pressure side winglet is the lowest

while the averaged film cooling effectiveness of this kind of tip is the highest when the film cooling holes are introduced. For the squealer tip with pressure side winglet

the influence region of coolant is affected by the distribution of the film cooling holes. Coolant from the camber-line cooling holes can effectively cool the cavity floor near the suction side

while coolant from the cooling holes in pressure-side winglet effectively cools the winglet surface and cavity floor near the pressure side.

关键词

Keywords

references

HAN J C, DUTTA S, EKKAD S. Gas turbine heat transfer and cooling technology [M]. 2rd ed. Baca Raton, EL, USA: Taylor & Francis Group, 2012: 94-106.

KWAK J S, HAN J C. Heat transfer coefficient on a gas turbine blade tip and near tip regions: 2002-3012 [R]. Reston, VA, USA: AIAA, 2002.

KWAK J S, HAN J C. Heat transfer coefficients on the squealer tip and near squealer tip regions of a gas turbine blade [J]. ASME Journal of Heat Transfer, 2003, 125(4): 669-677.

KWAK J S, HAN J C. Heat transfer coefficients and film-cooling effectiveness on the squealer tip of a gas turbine blade [J]. ASME Journal of Turbomachinery, 2003, 125(4): 648-657.

黄琰, 晏鑫, 何坤, 等. 气膜孔分布对常规凹槽叶顶传热和冷却性能的影响 [J]. 西安交通大学, 2016, 50(5): 101-107.

HUANG Yan, YAN Xin, HE Kun, et al, Effect of cooling-hole distributions on heat transfer and cooling effectiveness on turbine blade tip [J]. Journal of Xi'an Jiaotong University, 2016, 50(5): 101-107.

LEE S W, KIM S U, KIM K H. Aerodynamic performance of winglets covering the tip gap inlet in a turbine cascade [J]. International Journal of Heat and Fluid Flow, 2012, 34: 36-46.

LEDEZMA G A, ALLEN J, BUNKER R S. An experimental and numerical investigation into the effects of squealer blade tip modifications on aerodynamic performance [C]∥ASME 2013 Turbine Blade Tip Symposium. New York, USA: ASME, 2013: 2004.

ZHOU C, HODSON H, TIBBOTT I, et al. Effects of winglet geometry on the aerodynamic performance of tip leakage flow in a turbine cascade [J]. ASME Journal of Turbomachinery, 2013, 135(5): 051009.

YAN Xin, HUANG Yan, HE Kun, et al. Numerical investigations into the effect of squealer-winglet blade tip modifications on aerodynamic and heat transfer performance [J]. International Journal of Heat and Mass Transfer, 2016, 103: 242-253.

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