航空发动机涡轮轮缘密封优化  

Optimization of Turbine Rim Seals in Aero Engines

作　　者：马鸿 Ma Hong(Shaanxi Polytechnic Institute,Shaanxi Xianyang 712000)

机构地区：[1]陕西工业职业技术学院,陕西咸阳712000

出　　处：《内燃机与配件》2025年第4期13-15,共3页Internal Combustion Engine & Parts

基　　金：陕西工业职业技术学院自然科学类一般项目资助“蜂窝叶顶结构对涡轮叶栅密封的关键技术研究”(2024YKYB-005)。

摘　　要：针对某型涡扇发动机涡轮轮缘密封系统存在的问题,通过数值模拟和试验验证相结合的方法,系统研究了轮缘密封结构参数对气动特性的影响。结果表明,优化密封腔结构和增加密封齿数量可有效降低密封漏气量,提高密封效率。基于研究结果,提出了一种改进型轮缘密封结构,经验证可将密封漏气量降低18%,为航空发动机涡轮轮缘密封技术的改进提供了参考。Addressing issues in a turbine rim seal system of a specific turbofan engine,this study employs a combination of numerical simulation and experimental verification to systematically investigate the impact of rim seal structural parameters on aerodynamic characteristics.Results indicate that optimizing the seal cavity structure and increasing the number of seal teeth can effectively reduce seal leakage and improve sealing efficiency.Based on these findings,an improved rim seal structure is proposed,which has been verified to reduce seal leakage by 15%,providing a reference for the advancement of turbine rim seal technology in aero engines.

关 键 词：航空发动机 涡轮轮缘密封 气动特性 数值模拟 结构优化 

分 类 号：V23[航空宇航科学与技术—航空宇航推进理论与工程]