叶型探针对跨声压气机性能影响的数值模拟

Numerical Simulation Analysis of the Influence of a Blade Profile Probe on the Performance of a Transonic Compressor

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。

To reveal the physical mechanism controlling the influence of a blade profile probe on the aerodynamic performance of a transonic compressor,studied in detail was the variation law of the performance characteristics and the inner flow field of a compressor at its design speed before and after a probe is installed by using a 3-D numerical simulation method and through establishing a calculation model for a 1.5-stage compressor with a multi-point-real-entity probe.The research results show that after a probe is locally installed on a stator blade between stages,the flow rate of the compressor at the lower choke point decreases by 0.1%,the maximal efficiency drops by 0.4% and the flow rate at the stall point increases by 0.15%.A change of the attack angle of the stator blade caused by a change of the working point of the compressor constitutes an important factor influencing the area of the flow going around the probe at both sides of the blade surface and a relatively high correlation degree exists between the probe-going-around flow influencing extent and the aerodynamic load of the stator blade.A large area probe-around-going flow will exacerbate the radial migration and separation of the boundary layer at the root on the back of the blade at the downstreams of the rotor constitutues the root cause of the aerodynamic stall of the compressor at an earlier time.