低雷诺数高负荷低压涡轮叶型的气动设计  

Aerodynamic design of highly-loaded blade in low-pressure turbine with low Reynolds number

作　　者：杨林[1,2] 乔渭阳[1] 罗华玲[1] 母忠强[1] 侯伟涛[1] 

机构地区：[1]西北工业大学动力与能源学院,西安710072 [2]中国航空工业集团燃气涡轮研究院,成都610500

出　　处：《航空动力学报》2013年第5期1019-1028,共10页Journal of Aerospace Power

摘　　要：采用平面叶栅实验和数值模拟研究了不同负荷分布设计以及基于二维展向凹槽处理的非光滑型面设计对高负荷低压涡轮叶型流动损失的影响规律.研究表明:在低雷诺数状态下前加载负荷分布设计对高负荷低压涡轮叶型的二维气动性能更有利;二维展向凹槽处理的非光滑型面设计能够有效改善高负荷低压涡轮叶型在低雷诺数状态下的气动性能,但同时可在一定程度上恶化叶型在高雷诺数状态下的气动性能;基于二维展向凹槽处理的非光滑型面设计与后加载负荷分布设计的结合能够在更为宽广的雷诺数工况范围内改善叶型的气动性能.Study was carried out using the combination of numerical simulation and cascade experiment to understand the effects on flow loss from loading distribution design and non-smooth profile design based on two-dimension span-wise groove combined with loading distribution design.Research shows that fore-loaded design is superior to aft-loaded design in two-dimension aerodynamic performance under low Reynolds number conditions;non-smooth profile design based on two-dimension span-wise groove can improve aerodynamic performance at low Reynolds number,and decrease it at high Reynolds number;non-smooth profile design based on two-dimension span-wise groove combined with aft-loaded design can improve aerodynamic performance in wider range of Reynolds number.

关 键 词：气动设计 高负荷叶型 低压涡轮 低雷诺数 平面叶栅实验 数值模拟 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]