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 

机构地区：[1]Institute of Engineering Thermophysics,Chinese Academy of Sciences

出　　处：《Journal of Thermal Science》2014年第5期494-504,共11页热科学学报（英文版）

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

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 requirement.However,their bulky geometric size represents a more effective obstacle to flow from high pressure(HP) turbine rotor.These five struts give obvious influence for not only the LP turbine nozzle but also the flowfield within the ITD,and hence cause higher loss.Numerical 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 blades.According to the computational results,three main conclusions are finally obtained.Firstly,a noticeable low speed area is formed near the strut's leading edge,which is no doubt caused by the potential flow effects.Secondly,more severe radial migration of boundary layer flow adjacent to the strut's pressure side have been found near the nozzle's trailing edge.Such boundary layer migration is obvious,especially close to the shroud domain.Meanwhile,radial pressure gradient aggravates this phenomenon.Thirdly,velocity distribution along the strut's pressure side on nozzle's suction surface differs,which means loading variation of the nozzle.And it will no doubt cause nonuniform flowfield faced by the downstream rotor blade.

关 键 词：Intermediate Turbine Duct Integrated Design Concept Flowfield Analysis Total Pressure Loss Analysis 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]