燃气涡轮高负荷叶片冷却掺混损失研究  

Study on Cooling Mixing Loss of Gas Turbine Blade with High Load

作　　者：郭粲 孙添一 陈欣楠 李志刚[1] 李军[1,2] GUO Can;SUN Tianyi;CHEN Xinnan;LI Zhigang;LI Jun(Institute of Turbomachinery,Xi’an Jiaotong University,Xi’an 710049,China;Collaborative Innovation Center for Advanced Aero-Engine,Beijing 100191,China)

机构地区：[1]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 [2]先进航空发动机协同创新中心,北京100191

出　　处：《工程热物理学报》2024年第8期2306-2311,共6页Journal of Engineering Thermophysics

基　　金：国家科技重大专项资助项目(No.J2019-II-0022-0043)。

摘　　要：本文整理了近几年涡轮叶片气膜冷却掺混损失模型的发展历程和趋势,通过数值模拟的方法研究了吹风比以及孔排位置对于燃气涡轮高负荷叶片冷却掺混损失的影响,分析各部分气动损失的变化规律,结果表明,气膜冷却引起的掺混损失随吹风比迅速增加,前缘区域更为明显,高吹风比时不可忽略;吸力面的掺混损失要整体高于压力面,且越靠近前缘位置气膜冷却造成的损失就越大,为后续各个影响因素的整合,损失模型的深入研究提供了数据支持。The development and trend of the mixing loss model for film cooling of turbine blades in recent years are reviewed in this paper.The influence of the blowing ratio and the position of the holes on the mixing loss of high-load gas turbine blades is studied by numerical simulation.At the same time,the variation law of aerodynamic loss is analyzed.The results show that the mixing loss caused by film cooling increases rapidly with the blowing ratio,especially in the leading edge region,and can not be neglected at high blowing ratio.The mixing loss of suction surface is higher than that of pressure surface,and the loss caused by film cooling near the leading edge is larger.These provide data support for the integration of the following factors and the further study of the loss model.

关 键 词：涡轮叶片 掺混损失 数值模拟 吹风比 孔排位置 

分 类 号：V232.4[航空宇航科学与技术—航空宇航推进理论与工程] TK474.4[动力工程及工程热物理—动力机械及工程]