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为了缩短涡轮气动设计的周期,进一步发掘涡轮叶型的改进潜力,搭建了多级涡轮的翘曲S1流面气动优化平台.该平台具有速度快,周期短的特点.在考虑冷气的前提下,对多级叶片进行多层并行优化,避免了单列优化后叶列间匹配差的缺点,同时克服了多层S1流面的气动效率此消彼长的缺陷.对某型两级高压涡轮进行了气动优化设计,优化后10%,50%,90%叶高的S1流面的考虑冷气的气动效率分别提高了0.569%,0.490%,0.405%;第1级和第2级考虑冷气的气动效率分别提高了0.18%,0.05%;涡轮整体气动效率提高了0.15%;优化效果明显.经过分析可知,优化有效减小第1级导叶的通道横向二次流损失和第1级动叶的激波损失,第2级的原始叶型设计较为合理.下端壁喷射冷气是降低S1流面优化有效性的重要原因.
In order to shorten the cycle of turbine aerodynamic design and further explore the potential for improvement of turbine blades, a multi-stage turbine aerodynamic optimization platform with warped S1 flow surface is established. The platform has the advantages of fast speed and short cycle, Multilevel parallel optimization of multi-stage blades avoids the shortcomings of poor matching between leaflets after single-row optimization and overcomes the shortcoming of multi-layer S1 flow surface aerodynamic efficiency.In the case of a two-stage high-pressure turbine In the aerodynamic optimization design, the aerodynamic efficiencies of air-conditioning in the S1 surface with 10%, 50% and 90% of the leaf height after optimization are respectively increased by 0.569%, 0.490% and 0.405%, and the aerodynamic efficiencies of the first and second stages Respectively, increasing by 0.18% and 0.05% respectively; the overall aerodynamic efficiency of the turbine is improved by 0.15%; the optimization effect is obvious.According to the analysis, it is found that optimizing and effectively reducing the lateral secondary flow loss of the first- Wave loss, the original design of the second level of the leaf is more reasonable. Lower end wall spray air conditioning is to reduce the S1 flow surface optimization and effectiveness of the important reasons.