涡轮支板与导向器一体化气动设计方法研究  

Study on the Integrated Aerodynamic Design Method of Turbine Struts and Guide Vanes

作　　者：马广健 武晓龙[2] 陈云 王雷 MA Guang-jian;WU Xiao-long;CHEN Yun;WANG Lei(AECC Shenyang Engine Research Institute,Shenyang 110015,China;PLA Naval Consumer Representative Office of Engine in Shenyang,Shenyang 110043,China)

机构地区：[1]中国航发沈阳发动机研究所,沈阳110015 [2]海军驻沈阳地区发动机专业军事代表室,沈阳110043

出　　处：《航空发动机》2020年第2期9-15,共7页Aeroengine

基　　金：工信部民机预研项目资助。

摘　　要：针对大涵道比发动机低压涡轮设计要求,开展了大、小叶片组合叶栅形式的低压涡轮支板与导向器一体化设计方法研究。以常规参数化方法为基础,建立了大、小叶片设计参数关联关系,提出1种参数化程度高和参数关联性强的大、小叶片组合叶栅参数化叶型设计方法,并用于低压涡轮支板与导向器一体化气动方案设计。结果表明:涡轮支板与导向器一体化气动方案的总压恢复系数为0.981,叶片表面载荷分布合理,流场质量良好,叶栅出口流场参数分布均匀且周期性好。涡轮支板与导向器一体化叶型参数化设计方法具有良好的工程应用价值。Aiming at the design requirements of the low pressure turbine(LPT) of a certain high bypass ratio engine,the study on the integrated design method of the splitter combined cascade was carried out for the LPT struts and guide vanes.Based on the conventional parametric method,the incidence relation of splitter design parameters was established. A parametric blade design method for splitter with high parametric degree and strong parameter correlation was proposed for integrated aerodynamic scheme design of LPT struts and guide vanes.The results show that the total pressure recovery coefficient of the integrated aerodynamic scheme is 0.981. It is reasonable that blade surface load distribution and flow field quality is good, the flow field parameters at the outlet of the cascade are evenly distributed and has good periodicity. The parametric design method of blade type of turbine struts and guide vanes has good engineering application value.

关 键 词：大、小叶片 气动设计 参数化造型 大涵道比发动机 

分 类 号：V232.4[航空宇航科学与技术—航空宇航推进理论与工程]