Institute of Space and Aeronautical Science,University of Tokyo
雑誌名
ISAS report/Institute of Space and Aeronautical Science,University of Tokyo
巻
46
号
3
ページ
93 - 103
発行年
1981-02
抄録(英)
Nonuniformity of inlet flows through a test compressor stage has been studied based upon 3-D semi-actuator disk theory. The results show that the rotor blade vibration greatly influences the attenuation rate of distortion. The effects of the rotor/stator separation, the circumferential modal index and the tilting of the inlet distortion, are also demonstrated.