CAJ | 학술논문

采用商业软件CFX，在相对坐标系内数值模拟了不同出口马赫数下大焓降动叶的气动性能。数值结果表明，哈汽公司设计的大焓降动叶具有后加载特性，而且出口马赫数愈高，后加载特性愈明显。当动叶出口马赫数由0．47增加至0．81，总压损失系数在7．5％至14．5％之间变化。总的看来，大焓降动叶的变马赫数性能良好。
채용상업연건CFX，재상대좌표계내수치모의료불동출구마혁수하대함강동협적기동성능。수치결과표명，합기공사설계적대함강동협구유후가재특성，이차출구마혁수유고，후가재특성유명현。당동협출구마혁수유0．47증가지0．81，총압손실계수재7．5％지14．5％지간변화。총적간래，대함강동협적변마혁수성능량호。
Aerodynamic performance of highly-loaded rotor blade ,under different outlet mach numbers ,was researched in the relative coordinates by commercial software CFX .Numerical results showed that ,the low aspect ratio highly-loaded rotor blade designed by Harbin steam turbine company , has aft-loaded characteristics , and the higher outlet Mach number , the more obvious aft-loaded effect.When rotor blade outlet Mach number changes from 0.47 to 0.81, total pressure loss coefficient changes between 7.5%to 14.5%.In general,aerodynamic performance of the rotor blade is good under variable Mach number .