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以NASA Rotor35为研究对象,应用数值模拟手段深入分析了该转子在近失速工况的流动特征,针对其叶片吸力面附面层分离和上端壁处严重的二次流动,对比研究了叶表抽吸和上端壁抽吸对该转子流场结构以及气动性能的影响。计算结果表明:两种抽吸形式均使压气机的压比和效率有所提高。叶表抽吸可有效控制叶片通道激波,减小叶片吸力面的分离区,其最佳位置位于通道激波之后附面层发展处,在最佳抽吸量时压比提高了1.85%,效率提高了8.53%。上端壁抽吸有效地改善了近端壁区域的进出口气流角,其最佳位置位于叶片近前缘处,在最佳抽吸量时压比提高了0 86%,效率提高了4 54%。
Taking NASA Rotor35 as the research object, the flow characteristics of the rotor in near-stall condition are analyzed in detail by means of numerical simulation. According to the separation of the suction surface of the blade and the serious secondary flow at the upper end wall, Effects of suction and suction on the flow field structure and aerodynamic performance of the rotor. The calculation results show that the pressure ratio and the efficiency of the compressor are both increased by the two suction forms. Leaf table suction can effectively control the shock of leaf channel and reduce the separation area of leaf suction surface. The optimal position is located in the development of the adherent layer after the channel shock, and the pressure ratio increased by 1.85% Efficiency increased by 8.53%. The suction of the upper end wall effectively improves the inlet and outlet airflow angles of the proximal wall, and the best position is located near the leading edge of the blade. When the optimal suction amount is reached, the pressure ratio is increased by 86% and the efficiency is increased by 544%.