摘要
为研究转子叶片前缘倒角结构对涡轮轮缘密封性能的影响机制,在不同封严流量下,对转子前缘带倒角和不带倒角的轮缘密封装置进行数值模拟。研究结果表明:转子前缘倒角结构通过改变前缘附近压力势场从而对主流燃气入侵和封严出流冷气与主流的干涉产生影响。增加倒角结构有利于减弱主流高温燃气入侵的程度,在低封严流量下,最大可使得涡轮盘腔封严效率提高7%;倒角结构削弱了由封严间隙涡和马蹄涡形成的通道涡强度,降低封严冷气与主流干涉造成的气动损失。当封严流量为主流流量的1.3%时,带倒角装置的涡轮级气动效率增大2.1%。
In order to study the influence mechanism of the leading edge fillet of the rotor blade on the sealing performance of the turbine rim,the rim sealing devices with and without fillet at the leading edge of the rotor were numerically simulated under different sealing flow rates.The results show that the fillet structure of the rotor leading edge affects the intrusion of mainstream gas and the interference between the outlet cold air and the mainstream by changing the pressure potential field near the leading edge.The added fillet structure is beneficial to weaken the intrusion degree of mainstream high-temperature gas.Under low sealing flow,the sealing efficiency of turbine disk cavity can be increased by 7%;the fillet structure weakens the strength of the channel vortex formed by the seal gap vortex and horseshoe vortex,and reduces the aerodynamic loss caused by the interference between the seal cold air and the main stream.When the sealing flow is 1.3%of the main flow,the aerodynamic efficiency of the turbine stage with fillet device increases by 2.1%.
作者
白涛
杨青真
施永强
陈玲玲
解云琪
李怡
BAI Tao;YANG Qing-zhen;SHI Yong-qiang;CHEN Ling-ling;XIE Yun-qi;LI Yi(School of Power and Energy,Northwestern Polytechnical University,Xi an 710129,China;School of Aircraft,Xi an Aeronautical,Xi an 710077,China)
出处
《科学技术与工程》
北大核心
2022年第31期14019-14025,共7页
Science Technology and Engineering
基金
国家自然科学基金青年科学基金(12102356)。
