串列叶片气动设计及优化
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LIU Bao-jie1，2, YU Xian-jun1，2, AN Guang-feng1，2, TAO Yuan3, ZHOU An-yu4, LI Li-li4 （1. Research Institute of Aero-Engine，Beihang University，Beijing 100191，China；2. National Key Laboratory of Science and Technolo⁃ gy on Aero-Engines，Beijing 100191，China；3. School of Aeronautical Engineering，Civil Aviation University of China，Tianjin 300300，
第 47 卷 第 4 期 2021 年 8 月
航空发动机
Aeroengine
Vol. 47 No. 4 Aug. 2021
串列叶片气动设计及优化
刘宝杰 1，2，于贤君 1，2，安广丰 1，2，陶 源 3，周安宇 4，李丽丽 4
（1. 北京航空航天大学 航空发动机研究院，北京 100191；2. 航空发动机气动热力国防科技重点实验室，北京 100191； 3. 中国民航大学 航空工程学院，天津 300300；4. 中国航发沈阳发动机研究所，沈阳 110015）
China；4. AECC Shenyang Engine Research Institute，Shenyang 110015，China） Abstract：In order to further improve the load level of fan / compressor，the tandem blades were studied. The load advantage range of tandem blades relative to conventional blades was analyzed by theoretical method，and the comparative test was carried out on a low-speed large-scale compressor test rig. The results show that when the load factor is greater than 0.46，tandem blades show obvious advantages， and the load factor of 0.46 can be regarded as the critical point of the dominant range of tandem blades. The interaction mechanism between the forward and aft rows of subsonic and supersonic tandem profile was analyzed by numerical simulation. The flow control principle and op⁃ timization design idea of tandem profile were summarized. The optimization design results of typical subsonic and supersonic profile were given. The results show that the design point losses of the optimized subsonic and supersonic tandem profile are reduced by 6% and 20% re⁃ spectively，and the available attack angle ranges are widened by 2° and 0.5° respectively. The design demonstration of the double-stage fan tandem blade outlet stage is completed with a load factor of 0.4. The results show that compared with the conventional scheme，the pressure ratio of the tandem blade scheme is significantly improved，and the blocking flow and isentropic efficiency are also significantly improved in the common speed range. Key words：tandem profile；tandem blade；high-load；compressor/fan design；aeroengine
摘要：为了进一步提高风扇/压气机的负荷水平，对串列叶片进行了研究。采用理论方法分析了串列叶片相对于常规叶片的
负荷优势区间，并利用低速大尺寸压气机试验台进行了对比试验验证。结果表明：当负荷系数大于 0.46 时，串列叶片表现出明显
的优势，可以将负荷系数拟方法分析了亚声速和超声速串列叶型前后排的
相互影响机制，总结了串列叶型流动控制原则和优化设计思路，给出了典型亚声速和超声速叶型的优化设计结果。结果表明：优
化后的亚声速和超声速串列叶型设计点损失分别减少了 6% 和 20%，可用攻角范围分别拓宽了 2°和 0.5°。完成了负荷系数为 0.4
的双级风扇串列叶片出口级方案设计论证。结果表明：与常规方案相比，在常用转速范围内，串列叶片方案的压比明显提高，中低
转速堵塞流量和等熵效率也明显提高。
关键词：串列叶型；串列叶片；高负荷；压气机/风扇设计；航空发动机
中图分类号：V231.3
文献标识码：A
doi：10.13477/ki.aeroengine.2021.04.005
Aerodynamic Design and Optimization of Tandem Blades
第 47 卷 第 4 期 2021 年 8 月
航空发动机
Aeroengine
Vol. 47 No. 4 Aug. 2021
串列叶片气动设计及优化
刘宝杰 1，2，于贤君 1，2，安广丰 1，2，陶 源 3，周安宇 4，李丽丽 4
（1. 北京航空航天大学 航空发动机研究院，北京 100191；2. 航空发动机气动热力国防科技重点实验室，北京 100191； 3. 中国民航大学 航空工程学院，天津 300300；4. 中国航发沈阳发动机研究所，沈阳 110015）
China；4. AECC Shenyang Engine Research Institute，Shenyang 110015，China） Abstract：In order to further improve the load level of fan / compressor，the tandem blades were studied. The load advantage range of tandem blades relative to conventional blades was analyzed by theoretical method，and the comparative test was carried out on a low-speed large-scale compressor test rig. The results show that when the load factor is greater than 0.46，tandem blades show obvious advantages， and the load factor of 0.46 can be regarded as the critical point of the dominant range of tandem blades. The interaction mechanism between the forward and aft rows of subsonic and supersonic tandem profile was analyzed by numerical simulation. The flow control principle and op⁃ timization design idea of tandem profile were summarized. The optimization design results of typical subsonic and supersonic profile were given. The results show that the design point losses of the optimized subsonic and supersonic tandem profile are reduced by 6% and 20% re⁃ spectively，and the available attack angle ranges are widened by 2° and 0.5° respectively. The design demonstration of the double-stage fan tandem blade outlet stage is completed with a load factor of 0.4. The results show that compared with the conventional scheme，the pressure ratio of the tandem blade scheme is significantly improved，and the blocking flow and isentropic efficiency are also significantly improved in the common speed range. Key words：tandem profile；tandem blade；high-load；compressor/fan design；aeroengine
摘要：为了进一步提高风扇/压气机的负荷水平，对串列叶片进行了研究。采用理论方法分析了串列叶片相对于常规叶片的
负荷优势区间，并利用低速大尺寸压气机试验台进行了对比试验验证。结果表明：当负荷系数大于 0.46 时，串列叶片表现出明显
的优势，可以将负荷系数拟方法分析了亚声速和超声速串列叶型前后排的
相互影响机制，总结了串列叶型流动控制原则和优化设计思路，给出了典型亚声速和超声速叶型的优化设计结果。结果表明：优
化后的亚声速和超声速串列叶型设计点损失分别减少了 6% 和 20%，可用攻角范围分别拓宽了 2°和 0.5°。完成了负荷系数为 0.4
的双级风扇串列叶片出口级方案设计论证。结果表明：与常规方案相比，在常用转速范围内，串列叶片方案的压比明显提高，中低
转速堵塞流量和等熵效率也明显提高。
关键词：串列叶型；串列叶片；高负荷；压气机/风扇设计；航空发动机
中图分类号：V231.3
文献标识码：A
doi：10.13477/ki.aeroengine.2021.04.005
Aerodynamic Design and Optimization of Tandem Blades