Influence of the Number of Circumferential Nozzles on the Flow and Heat Transfer Characteristics of Swirl Cooling

doi:10.7652/xjtuxb201807014

您当前的位置：

首页 >

文章列表页 >

Influence of the Number of Circumferential Nozzles on the Flow and Heat Transfer Characteristics of Swirl Cooling

更新时间：2025-07-09

- Influence of the Number of Circumferential Nozzles on the Flow and Heat Transfer Characteristics of Swirl Cooling
- Vol. 52, Issue 7, Pages: 94-100(2018)
- 作者机构：
  
  西安交通大学叶轮机械研究所,西安,710049
- 作者简介：
- 基金信息：
- DOI：10.7652/xjtuxb201807014
  CLC： TK474.7
- Online First：10 July 2018，
  
  Published：2018
- 稿件说明：
移动端阅览
Influence of the Number of Circumferential Nozzles on the Flow and Heat Transfer Characteristics of Swirl Cooling[J]. 2018, 52(7): 94-100.
DOI：

Influence of the Number of Circumferential Nozzles on the Flow and Heat Transfer Characteristics of Swirl Cooling[J]. 2018, 52(7): 94-100. DOI： 10.7652/xjtuxb201807014.

摘要

为了研究在旋流腔周向布置多个喷嘴对旋流冷却特性的影响

分别建立了保持喷嘴几何尺寸不变和保持喷嘴进口总面积不变的旋流冷却模型。在相同质量流量和喷嘴长宽比的条件下

采用数值计算方法

研究了周向喷嘴数对旋流冷却特性的影响

并分析、对比了两种情况下旋流冷却性能的差异。研究结果表明:当保持喷嘴几何尺寸不变时

靶面平均Nu随周向喷嘴数增加而逐渐减小

但靶面Nu分布更加均匀

由于下游冷气速度受轴向横流影响较大

高Nu区向下方偏移

旋流腔冷气涡数目随周向喷嘴数增多而逐渐减少

冷气总压损失也随之减少; 当保持喷嘴进口总面积不变时

随着周向喷嘴数的增加

靶面高Nu区面积和靶面平均Nu先增大然后略有减小

都在周向喷嘴数为2时达到最大值。由于下游冷气速度受轴向冲击影响较小

在旋流腔轴向下游处

靶面展向平均Nu略有提高

而总压损失随着周向喷嘴数的增加逐渐增加。

Abstract

To study the effects of the number of circumferential nozzles in vortex chamber on the swirl cooling characteristics

two swirl cooling models were established

keeping the nozzle geometry and the total area of the nozzle inlets unchanged

respectively. At the same mass flow rate and nozzle aspect ratio

the effects of the number of circumferential nozzles on the swirling cooling characteristics were studied by numerical method

and the difference of swirling cooling performance between the two models were compared and analyzed. Results revealed that when the nozzle geometry is unchanged

the target average Nusselt number decreases with the number of nozzles

but the target Nusselt number distribution becomes more uniform. As the downstream air speed is more affected by the axial flow

the high Nusselt number region deflects downward. The number of air vortexes in vortex chamber decreases due to the increase in the number of nozzles

and the total pressure loss also decreases. When the total area of the nozzle inlets is unchanged

as the number of nozzles increases

the area of target high Nusselt number region and the average Nusselt number at first increase and then decrease

and become the largest when the number of nozzles is two. Because the downstream air velocity is less affected by the impact of axial flow

the target spanwise average Nusselt number has a small increase in the axial downstream

while the total pressure loss increases with the number of circumferential nozzles.

关键词

Keywords

references

翁史烈, 王永泓, 宋华芬, 等. 现代燃气轮机装置 [M]. 上海: 上海交通大学出版社, 2015: 1-10.

LIGRANI P M, OLIVEIRA M M, BLASKOVICH T. Comparison of heat transfer augmentation techniques [J]. AIAA Journal, 2003, 41(3): 337-362.

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

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.

LIGRANI P M, HEDLUND C R, THAMBU R, et al. Flow phenomena in swirl chambers [J]. Experiments in Fluids, 1998, 24(3): 254-264.

KHALATOV A A, BORISOV I I, SEVERIN S D, et al. Heat transfer hydrodynamics and pressure drop in the model of a blade leading edge cyclone cooling [C]∥ Proceedings of ASME Turbo Expo 2011. New York, USA: ASME, 2011: 1057-1065.

DU Changhe, LI Liang, LI Sen, 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.

DU Change, LI Liang, WU Xin, et al. Effect of jet nozzle geometry on flow and heat transfer performance of vortex cooling for gas turbine blade leading edge [J]. Applied Thermal Engineering, 2016, 93: 1020-1032.

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.

MOUSAVI S M, GHADIMI B, KOWSARY F. Numerical study on the effects of multiple inlet slot configurations on swirl cooling of a gas turbine blade leading edge [J]. International Communications in Heat and Mass Transfer, 2018, 90: 34-43.

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]∥ASME Turbo Expo 2006: Power for Land, Sea, and Air. New York, USA: ASME, 2006: 325-340.

杜长河, 李森, 李亮, 等. 叶片前缘旋流蒸汽冷却流动和传热的数值研究 [J]. 西安交通大学学报, 2015, 49(10): 72-78.

DU Changhe, LI Sen, LI Liang, et al. Numerical study on characteristics of flow and heat transfer of steam vortex cooling for blade leading edges [J]. Journal of Xi'an Jiaotong University, 2015, 49(10): 72-78.

Views

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

Catalytic Cracking of Ammonia for Ammonia-Hydrogen Co-Firing in Gas Turbines

Visualization Experimental Study on the Influence of Orifice Diameter on Methanol Flow and Transient Spray Characteristics in High-Pressure Injection Nozzles

Study on the Applicability of Turbulence Model to Transient Evolution Characteristics of Cloud Cavitation in Nozzle

Uncertainty Quantification and Sensitivity Analysis on Aerodynamic Performance of Gas Turbine Exhaust Diffuser

Study on the Aerodynamic Performance of Gas Turbine Exhaust Diffuser Coupled with Last Stage Turbine

Related Author

SI Gengfan

XIAO Tong

ZHANG Meng

WANG Jinhua

HUANG Zuohua

ZHANG Ying

LI Hongmei

HAN Dan

Related Institution

State Key Laboratory of Multiphase Flow in Power Engineering，Xi’an Jiaotong University

National Key Laboratory of Marine Engine Science and Technology, China State Shipbuilding Corporation Limited

Shanghai Marine Diesel Engine Research Institute, China State Shipbuilding Corporation Limited

Key Laboratory for Power Machinery and Engineering of the Ministry of Education, Shanghai Jiao Tong University

Institute of Energy Research, Jiangsu University

⁰