间隙阻尼结构对轮缘密封封严效率和气动性能影响的数值研究  

Numerical Study on Effects of Clearance-Damping Structure on theSealing Effectiveness and Aerodynamic Performance of Rim Seal

作　　者：雷隆 屈杰[1,2,3] 高庆 李志刚 李军[2] LEI Long;QU Jie;GAO Qing;LI Zhigang;LI Jun(Xi’an TPRI Energy Conservation Technology Co.,Ltd.,Xi’an Thermal Power Research Institute Co.,Ltd.,Xi’an 710054,China;Institute of Turbomachinery,Xi’an Jiaotong University,Xi’an 710049,China;State Key Laboratory of High-Efficiency Flexible Coal Power Generation and Carbon Capture Utilization and Storage,Beijing 102209,China)

机构地区：[1]西安热工研究院有限公司西安西热节能技术有限公司,西安710054 [2]西安交通大学叶轮机械研究所,西安710049 [3]高效灵活煤电及碳捕集利用封存全国重点实验室,北京102209

出　　处：《西安交通大学学报》2025年第5期143-155,共13页Journal of Xi'an Jiaotong University

基　　金：国家科技重大专项资助项目(J2019-Ⅱ-0010-0030)。

摘　　要：为提高燃气轮机透平轮缘密封封严效率,以某型燃气透平第一级动静叶栅和动叶前盘腔轮缘密封为研究对象,设计了4种间隙阻尼轮缘密封结构,在5种工况下对比了原始结构和4种间隙阻尼结构的封严效率、非定常流动特征和盘腔下游动叶通道出口的总压损失系数。结果表明:在5种工况下,4种间隙阻尼结构的封严效率均优于原始结构,间隙内动盘凸肩结构的封严效率最高,其次为静盘凸肩动盘凹槽结构;与原始结构相比,5种工况下动盘凸肩结构在外腔静盘面测点处封严效率分别提高了47.1%、51.6%、32.4%、25.4%和26.2%;从流动机理角度分析,凸肩结构缩短了轮缘间隙长度,限制了燃气入侵通流面积,同时凸肩结构内的微小通道内形成了许多涡系,增大了燃气向内入侵的流动阻力,使封严效率大幅提高;在5种工况下,动盘凸肩结构在动叶栅出口端部的总压损失系数与原始结构相比分别增大了2.2%、1.6%、1.6%、2.5%和3.0%,相较于该结构大幅提高盘腔封严效率的表现而言,增加的气动损失相对较小。In order to further improve the sealing effectiveness of rim seals in gas turbines,with the focus of the stationary and rotating blade cascades of the first stage,as well as the rim seal of the front disk cavity of the moving blades in a certain type of gas turbine,four clearance-damping rim seal structures are designed.Under five seal coolant flow rate operating conditions,the sealing effectiveness,unsteady flow characteristics,and total pressure loss coefficient at the downstream moving blade passage of the original structure and the four clearance-damping structures were compared.The results show that under the five operating conditions,the sealing effectiveness of the four clearance-damping structures is superior to that of the original structure.The rotor protruding shoulder structure in the clearance exhibits the best sealing performance,followed by the stator protruding shoulder structure and the rotor groove structure.Compared with the original structure,under the five operating conditions,the average sealing effectiveness of the rotor protruding shoulder structure at the monitoring point on stator surface of the outer cavity increases by 47.1%,51.6%,32.4%,25.4%,26.2%,respectively.From the perspective of the flow mechanism,the protruding shoulder structure shortens the rim clearance length and restricts the flow area for gas ingestion.Meanwhile,numerous vortices form within the micro-channels of the protruding shoulder structure,increasing the flow resistance for gas ingestion inward,thereby significantly improving the sealing effectiveness.Under the five operating conditions,the total pressure loss coefficients at the blade cascade exit endwall region for the rotor protruding shoulder structure increase by 2.2%,1.6%,1.6%,2.5%,3.0%,respectively,compared with the original structure.Compared with the significant improvement in cavity sealing effectiveness achieved by this structure,its impact on aerodynamic losses is relatively small.

关 键 词：燃气透平 轮缘密封 阻尼结构 封严性能 总压损失 

分 类 号：TK474.7[动力工程及工程热物理—动力机械及工程]