摘要
本文借助S1/S2两类流面迭代和S1流面正反问题混合计算方法,以叶片吸力面边界层吸气为手段,设计了一高负荷跨声速压气机叶型,同时利用MISE软件详细分析了稠度和最大相对厚度对叶片吸力面边界层吸气结构参数的影响。结果表明,叶片吸力面边界层吸气能够显著地改善跨声速压气机叶栅气动性能,并且最优吸气位置与叶型最大相对厚度和稠度有关,但最优吸气量受叶型参数的影响较小。
In order to increase the pressure ratio of axial compressor stages, the iterative method between S1/S2 relative stream surfaces is implemented, and boundary layer suction to control flow separation is introduced into the process of blade design. An example of a single stage axial compressor is given using such methods, the analytic result shows that the optimal suction location is relative to the maximum relative thick- ness and consistence, but the optimal suction mass - flow rate has little relative to the blade profile parameters.
出处
《燃气轮机技术》
2008年第3期29-32,57,共5页
Gas Turbine Technology
关键词
吸附式压气机
叶型损失
吸气位置
吸气量
最大相对厚度
稠度
aspirated compressors
profile loss
sustion location
suction mass - flow rate
max relative thickness
consistence
