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为揭示叶型探针对跨声压气机气动性能影响的物理机理,采用三维数值模拟方法,通过构建带多点实体探头的1.5级压气机计算模型,详细研究了设计转速下压气机在安装探头前后性能特性与内部流场的变化规律。结果表明:级间局部静叶安装探头后,压气机下堵点流量减小0.1%,最高效率降低0.4%,失速点流量增大0.15%;由压气机工作点改变所引起的静叶攻角变化是影响叶片表面两侧探头绕流尺度的重要因素,并且探头绕流影响程度与静叶气动负荷存在较高的关联度;探头大尺度绕流加剧下游转子叶背根部附面层径向迁移与分离是导致该型压气机气动失稳提前的主要原因。
In order to reveal the physical mechanism of the influence of leaf probe on the aerodynamic performance of transonic compressor, a three-dimensional numerical simulation method was used to build a 1.5-level compressor model with multi-point solid probe. Before and after the performance characteristics and internal flow field changes. The results show that after the probe is mounted on the interstage local vane, the flow rate at the lower plug point of the compressor is reduced by 0.1%, the maximum efficiency is reduced by 0.4% and the flow rate at the stall point is increased by 0.15%. The angle of attack of the static blade due to the change of the working point of the compressor Variations are the important factors affecting the flow around the blade on both sides of the blade surface, and the degree of influence of the probe flow around the flow and static aerodynamic load there is a high correlation; probe large scale flow exacerbated the downstream rotor dorsal root radial migration With the separation is the main reason leading to the aerodynamic instability of the compressor.