Effects of Nozzle-Strut Integrated Design Concepton on the Subsonic Turbine Stage Flowfield

作     者：LIU Jun DU Qiang LIU Guang WANG Pei ZHU Junqiang 

作者机构：Institute of Engineering ThermophysicsChinese Academy of Sciences 

出 版 物：《Journal of Thermal Science》 (热科学学报（英文版）)

年 卷 期：2014年第23卷第5期

页      面：494-504页

核心收录：

学科分类：082502[工学-航空宇航推进理论与工程] 08[工学] 0805[工学-材料科学与工程（可授工学、理学学位）] 0825[工学-航空宇航科学与技术] 0702[理学-物理学] 

基　　金：supported by grants from the National Natural Science Foundation of China(No.51306177) 

主　　题：集成设计 涡轮机 内流场 喷嘴 轻钢 亚音速 转子叶片 低压涡轮 

摘      要：In order to shorten aero-engine axial length,substituting the traditional long chord thick strut design accompanied with the traditional low pressure(LP) stage nozzle,LP turbine is integrated with intermediate turbine duct(ITD).In the current paper,five vanes of the first stage LP turbine nozzle is replaced with loaded struts for supporting the engine shaft,and providing oil pipes circumferentially which fulfilled the areo-engine structure ***,their bulky geometric size represents a more effective obstacle to flow from high pressure(HP) turbine *** five struts give obvious influence for not only the LP turbine nozzle but also the flowfield within the ITD,and hence cause higher *** investigation has been undertaken to observe the influence of the Nozzle-Strut integrated design concept on the flowfield within the ITD and the nearby nozzle *** to the computational results,three main conclusions are finally ***,a noticeable low speed area is formed near the strut s leading edge,which is no doubt caused by the potential flow ***,more severe radial migration of boundary layer flow adjacent to the strut s pressure side have been found near the nozzle s trailing *** boundary layer migration is obvious,especially close to the shroud ***,radial pressure gradient aggravates this ***,velocity distribution along the strut s pressure side on nozzle s suction surface differs,which means loading variation of the *** it will no doubt cause nonuniform flowfield faced by the downstream rotor blade.