考虑冷气的多级涡轮翘曲<i>S</i><sub>1</sub>流面的气动优化

王龙飞; 王松涛; 罗磊; 卢少鹏; 温风波

doi:10.13224/j.cnki.jasp.2015.07.023

考虑冷气的多级涡轮翘曲S₁流面的气动优化

doi: 10.13224/j.cnki.jasp.2015.07.023

哈尔滨工业大学能源科学与工程学院发动机气体动力研究中心, 哈尔滨 150001

基金项目:

国家自然科学基金委创新研究群体(51121004)

详细信息

作者简介:
王龙飞(1987-),男,山东济宁人,博士生,主要从事涡轮叶片内部冷却和冷却对气动性能影响的研究.

中图分类号: V231.1
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出版历程
- 收稿日期: 2014-01-13
- 刊出日期: 2015-07-28

Aerodynamic optimization for twisted S₁ stream surface of multi-stage turbine considering cooling air

Engine Aerodynamic Research Center, School of Energy Science and Engineering, Harbin Institute of Technology, Harbin 150001, China

摘要

摘要: 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.
- 叶型优化 /
- 翘曲S₁流面 /
- 多级涡轮 /
- 冷气掺混 /
- 气动效率
Abstract: To shorten the turbine aerodynamic design cycle and further explore the potential improvement of turbine blades, an aerodynamic optimization platform of twisted S₁ stream surface for multi-stage turbine with advantages of fast speed and short design period was presented. The platform could conduct multilayer parallel optimization for multi-column blades under the premise of cooling air, avoid disadvantage of poor matching between blade columns in single column optimization, and overcome the defect of aerodynamic efficiency shift for multilayer S₁ stream surface. A two stage high pressure turbine has been optimized; the results showed that, aerodynamic efficiency considering cooling air of three S₁ stream surfaces of 10%, 50%, 90% blade spanwise height was increased by 0.569%, 0.490% and 0.405%, the first stage and second stage aerodynamic efficiency considering cooling was improved by 0.18% and 0.05%, and aerodynamic efficiency considering cooling air of the turbine was increased by 0.15%, showing the significant effect of optimization. The analysis indicated that, the optimization reduced the channel transverse secondary flow loss of first stage stator blades and the shock loss of first stage rotor blades effectively, and the original blade design of turbine second stage was more reasonable. Coolant injection of flow channel hub was the important reason to reduce the effectiveness of S₁ stream surface optimization.
- blade profile optimization /
- twisted S₁ stream surface /
- multi-stage turbine /
- cooling air mixing /
- aerodynamic efficiency

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