基于反问题的涡轮过渡流道支板设计方法  

Design of Struts in an Intermediate Turbine Duct Based on Inverse Method

作　　者：侯朝山[1] 吴虎[1] 刘昭威 

机构地区：[1]西北工业大学动力与能源学院,陕西西安710072

出　　处：《西北工业大学学报》2017年第2期246-251,共6页Journal of Northwestern Polytechnical University

基　　金：国家自然科学基金(51076131)资助

摘　　要：涡轮过渡流道支板通常采用直叶型设计以保证其足够的强度,当流道进口旋流角度沿径向分布变化较大时,过渡流道内部容易发生气流分离,为此提出了基于三维黏性反问题设计方法的涡轮过渡流道低负荷整流支板设计。对某型涡扇发动机涡轮过渡流道整流支板进行了反问题设计,数值模拟结果表明,基于反问题设计的整流支板有利于抑制支板表面附面层增厚,降低过渡流道内部发生气流分离的风险,且新设计的过渡流道静压恢复系数系数增大了18.8%,总压损失系数降低了25.8%。In order to ensure the strength of strut in intermediate turbine duct （ ITD）, straight blade is usually used as the standard shape to the strut design. However, flow separation is likely to occur swirl angle has been found from hub to shroud. The concept of low load strut design is p when significant change in roposed based on the three- dimensional inverse design method theories. In the present work, the inverse design method has been applied to the strut design in a turbofan engine ITD. The numerical simulation results show that the inverse design strut is able to restrain the thickening of the boundary layer which can result in reducing the risk of flow separation. Additionally, the static pressure recovery coefficient of the new duct increases by 18.8% and the total pressure loss coefficient de- creases by 25.8%.

关 键 词：涡轮过渡流道 整流支板 反问题设计 气流分离 马赫数 

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]