跨声速压气机转子前缘积叠线的数值优化设计  

The Numerical Optimization Design of Stacking Line at the Rotor's Leading Edge of Transonic Compressor

作　　者：孙晓东[1] 王曦娟 王凯[3] 

机构地区：[1]哈尔滨汽轮机厂有限责任公司,哈尔滨150046 [2]哈尔滨动力设备股份有限公司,哈尔滨150040 [3]哈尔滨工业大学,哈尔滨150001

出　　处：《汽轮机技术》2009年第4期255-256,317,共3页Turbine Technology

摘　　要：采用数值优化方法对跨声速压气机转子NASA rotor37前缘积叠线进行了数值优化设计。本优化设计以绝热效率为目标函数,总压比与质量流量为约束条件,进行单目标有约束的优化设计。详细地分析对比了几何形状、总体性能及流场的变化。结果表明,叶片后掠并且加入弯曲,其激波的波形变得倾斜。在中部,强度有所削弱;在底部区域,激波有所后掠。同时指出,单一工况点的设计对变工况性能的控制能力不足。The numerical optimization design was carried out on the stacking line of the rotor of transonic compressor NASA rotor37. The objective function is adiabatic efficiency, and the constraint condition is the tOtal pressure ratio and mass flow. Then, the changes of geometry, overall performance and flow field were analyzed and compared in detail. The result shows that backward swept bowed blades leads to the inclination of the shock waveform. At the mid - span, the intensity of shock wave has been weaken; at hub, the shock wave has been moved backward. At the same time, it points out that single condition point design has shortage on control the off-design performance.

关 键 词：压气机 转子 优化设计 质量流量 

分 类 号：TK472[动力工程及工程热物理—动力机械及工程]