小展弦比涡轮叶片的弯曲优化设计  

Curve optimization design of a turbine blade withlow aspect ratio

作　　者：韩俊[1] 温风波[1] 赵广播[1] 

机构地区：[1]哈尔滨工业大学能源科学与工程学院,哈尔滨150001

出　　处：《清华大学学报（自然科学版）》2014年第1期102-108,共7页Journal of Tsinghua University(Science and Technology)

基　　金：国家自然科学基金青年科学基金项目(51206034)

摘　　要：该文重点讨论弯扭叶片设计方法在小展弦比的涡轴发动机涡轮叶片设计中的应用,旨在通过多方案的弯曲设计分析具有强二次流动的涡轮叶片的弯曲优化所能带来的气动性能改善和流场结构变化。给出了弯高固定而弯角不同的14个叶片弯曲设计方案。通过数值模拟计算分析了这些方案中总压比和流量,初步得出在该叶片设计中反弯设计要优于正弯和直叶片设计,且反弯15°方案为最优方案。根据密流沿叶高分布图分析了正弯、直和反弯叶片情况的下端区和中间区域的通流能力变化。结合叶片壁面极限流线图和静压分布,可发现反弯情况下造成的反向C型压力分布使得端区流动不但没有改善反而恶化,但是中间区域的低能流体却大大减少,从而总体损失得到减少。从出口截面的总压分布也可看出通道涡尺度变大,造成端区总压损失较大。The curved blade design method was used in a vortex axis engine turbine with low aspect ratio to analyze the effect of the curved blade optimization on improving the aerodynamic performance and the flow field structure of the turbine blade with strong secondary flow. Design schemes were determined for 14 curved blades with fixed height and different corners, with the total pressure ratio and flow then obtained through numerical calculation. Preliminary results showed that the negative curved blade prototype is superior to the positive and straight blades, and that the scheme with inflection of 15~ is the optimal solution. The changes of the flow ability in the bottom area and the middle area were given based on the density flow along the blade height. Combination of the blade wall limit flow and the static pressure distribution shows that the reverse C type pressure distribution caused by the negative curved blade deteriorates the end zone flow but with low energy fluid in the middle areas greatly reduced, so the overall losses are reduced. The total pressure distribution on the outlet section also shows that thetotal pressure loss in the end areas increases with increasing passage vortex scale.

关 键 词：涡轮 小展弦比 反弯叶片 通道涡 优化设计 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]