摘要
为获得跨声速涡轮全劈缝冷气对叶片尾缘激波的干涉特性,本文采用试验和数值方法研究尾缘波系结构在不同冷气量下的变化规律,并基于分区计算损失的方法,对激波损失、尾迹损失和边界层损失进行量化分析。结果表明,随冷气量增加,主流与冷气掺混过程发生变化,激波位置随之变化。在全劈缝冷气的作用下,压力侧尾缘膨胀波减弱,内尾波分解为两道弱激波,其中在70%冷气设计流量工况下,内尾波分解为强度相近的两道弱激波,激波损失最小;吸力侧尾缘膨胀波和分离激波消失,外尾波分解为一道弱激波和一系列压缩波。劈缝冷气可以降低叶栅通道总压损失,在130%冷气设计流量工况下叶栅总损失降低达32.95%。
In order to obtain the interference characteristics of vane trailing edge shock waves by transonic turbine trailing edge ejection,this paper adopts experimental and numerical methods to study the change rule of its trailing edge wave system structure under different cold gas flow rates,and quantitatively analyze the shock wave loss,trailing edge loss and boundary layer loss based on the zonal calculation of loss method.The results show that with the increase of cold air flow,the mixing process between the main stream and the cold air chang⁃es,and the position of the shock wave changes accordingly.The pressure side trailing edge expansion wave is weakened under the effect of the trailing edge ejection,and the inner tail wave is decomposed into two weak shock waves,in which the intensity of the twoweak shock waves are similar and the shock wave loss is minimized under the 70%cold air design flow condition.The suction-side trailing edge expansion wave and separation shock wave disappear,and the outer tail wave is decomposed into a weak shock wave and a series of compression waves.The trailing edge ejection reduces the total pressure loss of cascade channel,and the total pressure loss can be reduced by up to 32.95%under the 130%cold air design flow condition.
作者
杨建琦
高阿飞
张华良
尹钊
徐玉杰
陈海生
YANG Jianqi;GAO Afei;ZHANG Hualiang;YIN Zhao;XU Yujie;CHEN Haisheng(Institute of Engineering Thermophysics,Chinese Academy of Sciences,Beijing 100190,China;School of Engineering Science,University of Chinese Academy of Sciences,Beijing 100049,China;Nanjing Institute of Future Energy System,Institute of Engineering Thermophysics,Chinese Academy of Science,Nanjing 211135,China)
出处
《推进技术》
北大核心
2025年第9期80-91,共12页
Journal of Propulsion Technology
基金
国家科技重大专项(J2019-Ⅱ-0008-0028)
中国科学院洁净能源先导科技专项(XDA0400100)。
关键词
涡轮叶栅
全劈缝冷气
激波
尾迹
气动损失
Turbine cascade
Trailing edge ejection
Shock wave
Wake
Aerodynamic loss
