CAJ | 학술논문

本文以某重型燃气轮机压气机的跨音级为研究对象，利用NUMECA软件数值计算了跨音级压气机在不同转速下的特性曲线，并在设计转速下，对其内部流场进行了分析研究。研究发现，在跨音级动叶95％叶高截面，各工况均有激波产生，由近失速点向近阻塞点变化时，激波强度减弱，激波位置向下游移动，激波前后静压差减小，叶片负荷逐渐降低，高负荷区由前缘向尾缘移动。
본문이모중형연기륜궤압기궤적과음급위연구대상，이용NUMECA연건수치계산료과음급압기궤재불동전속하적특성곡선，병재설계전속하，대기내부류장진행료분석연구。연구발현，재과음급동협95％협고절면，각공황균유격파산생，유근실속점향근조새점변화시，격파강도감약，격파위치향하유이동，격파전후정압차감소，협편부하축점강저，고부하구유전연향미연이동。
A transonic compressor of heavy-duty gas turbine compressor is investigated by the NUMECA software in the paper and the performance curves at different rotational speeds are calculated , then the flow field in the compressor at design rotational speed is ana-lyzed.The research indicates that there are strong shock waves in the flow pass of 95%rotor section at each condition , the shock wave weakened with the situations change from near stall to near choke , differential pressure around the shock wave decreased , blade load reduced gradually and the high load moves to the trailing edge from the leading edge .