离心叶轮全三维反问题方法设计误差稳定性研究  

Numerical study on the design error stabilities of 3-dimensional streamline curvature inverse method for centrifugal impellers

作　　者：田晓沛[1] 单鹏[2] 

机构地区：[1]中国航空工业集团公司中航空天发动机研究院有限公司基础研究中心,北京101304 [2]北京航空航天大学能源与动力工程学院,北京100191

出　　处：《航空动力学报》2016年第5期1159-1169,共11页Journal of Aerospace Power

摘　　要：用流线曲率全三维反问题方法和引入滑移因子模型的准三维流线曲率反问题方法设计了叶片数不同的和增压比不同的小型高速离心叶轮.用商用计算流体力学(CFD)求解器估算了这些叶轮的性能.对比了这两种反问题方法的设计误差稳定性,考察了分流叶片对设计误差的影响.结果表明,流线曲率全三维反问题方法能够根据叶片负荷对叶片设计做出恰当调整.较准三维反问题方法,流线曲率全三维反问题方法所设计叶轮的增压比普遍偏高.随叶片负荷增加,较准三维反问题方法,流线曲率全三维反问题方法的设计误差变化较小,即其设计误差稳定性明显较好.分流叶片对准三维反问题方法设计结果的影响明显较小.Two groups of the high speed centrifugal impellers were both designed by the 3-dimensional streamline curvature inverse method and a quasi-3-dimensional inverse method with a slip factor model. One group had different blade numbers, while the other group had different total pressure ratios. The impeller performances were predicted by a commercial computational fluid dynamics （CFD） solver. The design error stabilities of the two methods were compared. The impacts of the splitter blades on the design errors were also studied. The results showed that the 3-dimensional streamline curvature inverse method could realize a proper adjustment to the blade shape according to the blade loading. And compared with the quasi-3-dimensional inverse method, the total pressure ratios of the impellers designed by the 3-dimensional streamline curvature inverse method were generally higher. Therefore, with the increase of blade loading, the design errors of the 3-dimensional streamline curva- ture inverse method changed much smaller than those of the quasi-3-dimensional inverse method; namely, the design error stability of the 3-dimensional streamline curvature inverse method was much better. In addition, for the quasi-3-dimensional method, the impacts of the splitter blades on the blade design results were much smaller.

关 键 词：设计误差稳定性 离心压气机 通流设计 流线曲率法 全三维反问题 数值研究 

分 类 号：V235[航空宇航科学与技术—航空宇航推进理论与工程]