| 可控扩散叶型的扩稳优化 |
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| 引用本文： | 徐全勇,阙晓斌,吴锋.可控扩散叶型的扩稳优化[J].航空动力学报,2017,32(7):1762-1768. |
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| 作者姓名： | 徐全勇 阙晓斌 吴锋 |
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| 作者单位： | 1.清华大学 航天航空学院，北京 100084 |
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| 基金项目： | 国家自然科学基金（51506108） |
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| 摘 要： | 采用正问题方法，将叶型几何参数化、叶型性能分析程序与遗传算法相结合，对某传统可控扩散叶型（CDA）进行叶型损失和攻角范围的综合性能优化设计。结果表明:优化叶型与原叶型具有相近的设计点损失，而其攻角范围由原来的11°增大至17.5°，其中负攻角范围增大了近4.5°。另外，优化叶型的损失随攻角变化也更为平缓，意味着可以在更为宽广的攻角范围内保持稳定的性能。分析表明:吸力面速度峰值位置由原叶型40%弦长处前移至20%弦长处，增加了减速区的长度，使减速更为平缓，是正攻角裕度增大的主要原因。负攻角裕度增加有两方面原因，优化叶型喉道面积增大且喉道位置与设计点吸力峰值位置错开，具有较大的堵塞裕度；压力面前部区域速度较为平缓，甚至略微加速，直至30%弦长后才开始减速扩压，避免了因压力面前缘处的较大速度尖峰以及随后的持续扩压导致附面层的过早分离。
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| 关 键 词： | 可控扩散 叶型设计 附面层转捩 优化 压气机 |
| 收稿时间： | 2015/10/22 0:00:00 |
Aerodynamic stability optimization of controlled diffusion airfoil |
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| XU Quanyong,QUE Xiaobin,WU Feng.Aerodynamic stability optimization of controlled diffusion airfoil[J].Journal of Aerospace Power,2017,32(7):1762-1768. |
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| Authors: | XU Quanyong QUE Xiaobin WU Feng |
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| Abstract: | Direct method was applied with an automatically optimization tool, in which the geometrical code and the blade to blade flow solver were integrated into genetic algorithm for searching of the optimal airfoil based on a conventional controlled diffusion airfoil(CDA). The design object was considered as a compromise of losses and operating range. It showed that the attainable incidence of optimized airfoil increased from 11° to 17.5° and the negative incidence range increased 4.5°, with similar design point loss as reference CDA airfoil. Additionally, the loss curve of optimized airfoil was flatter, showing it can remain stable performance in a wider working range. It indicated that the upstream propagation of suction peak shifted from 40% chord to 20% chord, extended the diffusion area and reduced the deceleration gradient, contributing to the increase of stall margin. The increase of negative incidence range can be ascribed to two reasons: first, the optimized airfoil has larger throat area and the throat location is apart from suction peak, thus gaining larger choking range. Secondly, the pressure surface velocity distribution is flatter, even with slight acceleration until 30% chord, as a result, the early separation of boundary layer caused by the leading edge spike and the following continual diffusion can be avoided. |
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| Keywords: | controlled diffusion airfoil design boundary layer transition optimization compressor |
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