级负荷系数为0.42的小流量轴流压气机 设计与试验验证

由于受限于“尺寸效应”,负荷增大使中小航空发动机压气机性能降低的特征较为明显,这对高负荷压气机设计提出了更大挑战.为深入研究小流量、高负荷轴流压气机,提出了2级高负荷轴流压气机的设计原则和总体要求.针对平均级负荷系数为0.42的高负荷特点,采用强根部、大反力度、低展弦比、叶片端弯和悬臂静子等气动设计方法以提高压气机性能.用全3D数值模拟方法对设计结果进行了校核,分析了其性能和流场结构.为了对设计、计算结果进行验证确认,对压气机进行了试验测量,计算与试验结果吻合良好.结果表明:高负荷轴流压气机设计点的压比为2.73,绝热效率为0.865,综合裕度为15.3％,达到了设计指标要求.

Design and Measurements for a Small Flow Rate Axial Compressor with Stage Work Coefficient of 0.42

The performance of axial compressors for small aeroengine decreases much remarkable as the load increases, due to so called "size effect", which raises the challenges for highly loaded compressors design. In order to study small flow rate and highly loaded axial compressors, the design guidelines and requirements of a 2-stage axial compressor were proposed. The aerodynamic design methods such as root-enhanced, large reaction, low aspect ratio, dihedral and cantilevered stator were employed aiming at improving the performance of the compressor with load coefficient up to 0.42. Three dimensional computational fluid dynamics(CFD) method was employed to validate the design and analyze the internal flow patterns. Experimental tests were performed to affirm the design and computation, the data agree well with CFD computation. Results show that the compressor has achieved the design pressure ratio of 2.73, adiabatic efficiency of 0.865 and comprehensive stall margin of 15.3%, which achieved the design targets.