静叶角度调节对组合压气机性能优化机理  

Stator setting angles adjustment on performance improvement of axial-centrifugal compressor

作　　者：曹志鹏[1] 刘波[2] 丁伟[2] 

机构地区：[1]北京航空航天大学能源与动力工程学院,北京100083 [2]西北工业大学动力与能源学院,西安710072

出　　处：《北京航空航天大学学报》2007年第8期878-881,893,共5页Journal of Beijing University of Aeronautics and Astronautics

摘　　要：采用流线曲率法求解组合压气机的准三维流场,在叶片排前后缘及中间设置计算站,使用样条函数拟合流线;根据组合压气机结构特点,发展了适合其特性计算的损失、落后角模型及计算程序;将特性计算程序与导、静叶角度优化调节方案相结合,确定出不同设计转速下,导、静叶最佳调节角度组合.在90%设计转速,近最高效率点处,利用全三维的数值模拟手段分析了组合压气机导、静叶最佳角度调节前后流场结构变化.研究结果表明:导、静叶角度调节削弱了压气机叶片排中的激波强度,减少了损失,同时能抑制气流的分离,明显改善组合压气机的流场结构.The quasi-three dimensional flow fields of axial-centrifugal compressor were solved with the streamline curvature method. Calculating stations were set in the leading edge, trailing edge and the middle of blade row. The streamline locations were fitted by cubic spline curves at each iteration computation. Perform- ance calculation codes with loss and deviation angle models were developed by using the methods mentioned above. Available loss and deviation angle models were selected by considering the special configuration of axial- centrifugal compressor. At different rotational speed, optimum angles of IGV and stator one were determined by stator vane angle adjustment method and performance analysis codes of axial-centrifugal compressor. At 90% design speed, peak efficiency, three-dimensional numerical simulations were performed for detail flow field analysis of axial-centrifugal compressor. Research results indicate that stator vane angle adjustment can weaken the intensity of shock wave, decrease the loss, prevent the air flow deviation of the blade surface, and improve the performance of axial-centrifugal compressor.

关 键 词：静叶角度调节 组合压气机 损失模型 落后角模型 特性曲线 

分 类 号：TK474.83[动力工程及工程热物理—动力机械及工程]