摘要
随着进口燃气温度的不断增大和燃烧室出口温度的均匀化,燃气涡轮端壁承受极高的热负荷。涡轮端壁处的复杂流动结构使端壁部分区域冷却困难,容易造成端壁烧蚀从而降低涡轮气动性能且威胁涡轮的安全运行。为了提高涡轮的冷却和气动性能,需要深入分析端壁附近的流动结构和传热冷却特性。本文以端壁冷却为出发点,对燃气涡轮的气动传热和冷却技术的发展进行总结分析,结合实验和数值计算结果,对端壁流动传热和冷却相关的先进实验和数值研究结果进行分析讨论。在此基础上,对涡轮端壁的先进冷却技术和非轴对称端壁下冷却结构优化进行了展望。
With the increase of the turbine inlet temperature and the uniformity of the temperature distribution at the outlet of the combustor,the turbine endwall endures the high thermal load due and the intensified turbulent flows.This is a great threat to the turbine safe operation.Therefore,the further study and understanding concerning the endwall aerothermal and cooling performance are of significant importance for the modern turbine design.This study aims to conclude the development of the aerothermal and cooling technologies for the turbine endwall.The detailed analyses regarding the advanced endwall cooling technique,the progressive and numerical methods the concerning the endwall heat transfer and cooling experimental have been conducted based on a lot of outstanding studies.In addition,the future development of the advanced cooling techniques and the optimization of the cooling configurations in a nonaxisymmetric contoured endwall are looked forward.
作者
杜昆
李军
宋立明
晏鑫
李志刚
DU Kun;LI Jun;SONG Liming;YAN Xin;LI Zhigang(Institute of Turbomachinery,Xi'an Jiaotong University,Xi'an 710049,China;Collaborative Innovation Center of Advanced Aero-Engine,Beijing 100191,China)
出处
《燃气轮机技术》
2018年第1期1-10,22,共11页
Gas Turbine Technology
基金
国家自然科学基金资助项目(51776151)
关键词
涡轮端壁
冷却结构
流动传热
实验测量
数值模拟
turbine endwall
cooling configurations
flow and heat transfer
experimental measurement
numerical simulation
