Effects of Nozzle Numbers and Temperature Ratios on Flow and Heat Transfer Characteristics of Vortex Cooling

doi:10.7652/xjtuxb201803003

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Effects of Nozzle Numbers and Temperature Ratios on Flow and Heat Transfer Characteristics of Vortex Cooling

更新时间：2025-07-09

- Effects of Nozzle Numbers and Temperature Ratios on Flow and Heat Transfer Characteristics of Vortex Cooling
- Vol. 52, Issue 3, Pages: 19-24+33(2018)
- 作者机构：
  
  西安交通大学能源与动力工程学院叶轮机械研究所,西安,710049
- 作者简介：
- 基金信息：
- DOI：10.7652/xjtuxb201803003
  CLC： TK474.7
- Online First：10 March 2018，
  
  Published：2018
- 稿件说明：
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Effects of Nozzle Numbers and Temperature Ratios on Flow and Heat Transfer Characteristics of Vortex Cooling[J]. 2018, 52(3): 19-24+33.
DOI：

Effects of Nozzle Numbers and Temperature Ratios on Flow and Heat Transfer Characteristics of Vortex Cooling[J]. 2018, 52(3): 19-24+33. DOI： 10.7652/xjtuxb201803003.

摘要

针对喷嘴数和温比对叶片前缘旋流冷却特性影响的问题

根据实际燃气轮机前缘结构进一步完善了旋流冷却模型

建立了含有进气腔室的旋流腔结构

采用数值模拟方法分析了喷嘴数和温比对旋流冷却特性的影响。研究时保持进口雷诺数和靶面温度不变

仅改变喷嘴数和温比。研究结果表明:进气腔室的引入使得喷嘴冷气沿流动方向逐渐增加。随着喷嘴数增加

喷嘴冷气流速降低

压力系数增加

流阻系数减小

换热强度降低但均匀性提高

综合换热因子增大。随着温比增加

喷嘴冷气流速增加

流阻系数减小

靶面热流密度降低

换热强度提高

综合换热因子增大。对于含有进气腔的叶片前缘冷却结构

推荐选取喷嘴数为6

温比范围为0.6～0.7。

Abstract

Aiming at the influences of the number of nozzles and temperature ratio on vortex cooling characteristics of gas turbine blade leading edge

a coolant chamber was added to establish a more reasonable vortex cooling configuration. Numerical method was used to investigate the flow and heat transfer behavior. The inlet Reynolds number and target temperature remained constant while the number of nozzles and temperature ratio were changed in the research. Results showed that the mass flow of air from nozzles increases along the flow direction with the introduction of coolant chamber. As the number of nozzles increases

the velocity of nozzle air

the friction coefficient and the heat transfer intensity decrease while the pressure coefficient

the uniformity of heat transfer intensity distribution and the thermal performance factor increase. As temperature ratio increases

the velocity of air from nozzles

the heat transfer intensity and the thermal performance factor increase

while the friction coefficient and the target heat flux decrease. For the gas turbine blade leading edge with the coolant chamber

the number of nozzles N=6 and the temperature ratio 0.6-0.7 are recommended.

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Keywords

references

HAN J C. Gas turbine heat transfer and cooling technology [J]. Proceedings of the National Heat Transfer Conference, 2001, 2: 1943-1946.

GLEZER B, MOON H K, O'CONNELL T. A novel technique for the internal blade cooling [C]∥Proceeding of ASME Turbo Expo 1996. New York, USA: ASME, 1996: V004T09A015.

KREITH F, MARGOLIS D. Heat transfer and friction in turbulent vortex flow [J]. Applied Scientific Research: Section A, 1959, 8(1): 457-473.

LING J P C W, IRELAND P T, HARVEY N W. Measurement of heat transfer coefficient distributions and flow field in a model of a turbine blade cooling passage with tangential injection [C]∥Proceeding of ASME Turbo Expo 2006. New York, USA: ASME, 2006: 325-340.

HEDLUND C R, LIGRANI P M, GLEZER B, et al. Heat transfer in a swirl chamber at different temperature ratios and Reynolds numbers [J]. International Journal of Heat and Mass Transfer, 1999, 42(22): 4081-4091.

HEDLUND C R, LIGRANI P M, MOON H K, et al. Heat transfer and flow phenomena in a swirl chamber simulating turbine blade internal cooling [J]. ASME Journal of Turbomachinery, 1999, 121(4): 804-813.

HEDLUND C R, LIGRANI P M. Local swirl chamber heat transfer and flow structure at different Reynolds numbers [J]. ASME Journal of Turbomachinery, 2000, 122(2): 375-385.

DU C, LI L, LI S, et al. Effects of aerodynamic parameters on steam vortex cooling behavior for gas turbine blade leading edge [J]. Proceedings of the Institution of Mechanical Engineers: Part A Journal of Power and Energy, 2016, 230(4): 354-365.

杜长河, 范小军, 李亮, 等. 喷射角度和喷嘴数对旋流冷却流动与传热特性的影响 [J]. 西安交通大学学报, 2016, 50(4): 76-80.

DU Changhe, FAN Xiaojun, LI Liang, et al. Influences of jet angle and jet nozzle number on flow and heat transfer characteristics of swirl cooling [J]. Journal of Xi'an Jiaotong University, 2016, 50(4): 76-80.

范小军, 杜长河, 李亮, 等. 4种冷却结构对叶片前缘流动换热影响的比较研究 [J]. 西安交通大学学报, 2017, 51(7): 37-43.

FAN Xiaojun, DU Changhe, LI Liang, et al. Comparative study of four cooling structures on flow and heat transfer behavior of blade leading edge [J]. Journal of Xi'an Jiaotong University, 2017, 51(7): 37-43.

徐亮,兰进,高建民,等.一种类螺纹孔结构的旋转射流换热特性数值模拟.2017,51(9):11-18.[doi:10.7652/xjtuxb2017 09002]

范小军,杜长河,李亮,等.4种冷却结构对叶片前缘流动换热影响的比较研究.2017,51(7):37-43.[doi:10.7652/xjtuxb 201707006]

杜长河,范小军,李亮,等.旋转半径和叶片安装角对动叶旋流冷却流动和传热特性的影响.2017,51(5):37-42.[doi:10.7652/xjtuxb201705006]

康蕊,厉彦忠,杨宇杰,等.轴向导热对板翅式换热器传热性能的影响.2017,51(2):140-148.[doi:10.7652/xjtuxb201702 022]

杜长河,范小军,李亮,等.抽吸孔对旋流和冲击冷却流动传热特性的影响.2017,51(1):19-24.[doi:10.7652/xjtuxb2017 01004]

张峰,王新军,李军.球凹平板冲击冷却性能的数值研究及结构改进.2016,50(1):124-130.[doi:10.7652/xjtuxb201601 019]

潘辉,冯松,刘朝晖,等.航空煤油RP-3热裂解结焦流动换热特性实验研究.2016,50(7):7-12.[doi:10.7652/xjtuxb2016 07002]

陈宇佳,杜长河,李亮.蒸汽冷却带肋矩形通道流动和换热特性数值研究.2016,50(3):62-67.[doi:10.7652/xjtuxb201603 010]

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