TY - GEN
T1 - Numerical simulations on a transonic axial-flow compressor rotor under clean and distorted inflows
AU - Fu, Lei
AU - Song, Xizhen
AU - Li, Qiushi
AU - Zhou, Sheng
PY - 2013
Y1 - 2013
N2 - The effects of circumferential distortions in inlet total pressure on the flow field in a low-aspect-ratio, high-speed, high-pressure-ratio, transonic compressor rotor are investigated in this paper. The flow field was studied numerically with and without inlet total pressure distortion. 3-D steady, unsteady numerical simulations have been conducted to determine the effects of circumferential total pressure inlet distortion on a transonic axial-flow compressor rotor. Overall performance (total pressure ratio, adiabatic efficiency and stable operating range) within inlet distortion has been investigated and compared with the results with clean inlet flow: Dropped in mass flow, adiabatic efficiency, and decreased in surge margin. Detail analyses of the flow field in the rotor show: Circumferential flow appears at the border of the distorted region, and flows inside to the distorted region. When entering the distortion, the blade passage faces a positive pre-swirl, on the countary, when leavinging the distortion, the blade passage faces a negative pre-swirl, which increases its incidence angle and loading.
AB - The effects of circumferential distortions in inlet total pressure on the flow field in a low-aspect-ratio, high-speed, high-pressure-ratio, transonic compressor rotor are investigated in this paper. The flow field was studied numerically with and without inlet total pressure distortion. 3-D steady, unsteady numerical simulations have been conducted to determine the effects of circumferential total pressure inlet distortion on a transonic axial-flow compressor rotor. Overall performance (total pressure ratio, adiabatic efficiency and stable operating range) within inlet distortion has been investigated and compared with the results with clean inlet flow: Dropped in mass flow, adiabatic efficiency, and decreased in surge margin. Detail analyses of the flow field in the rotor show: Circumferential flow appears at the border of the distorted region, and flows inside to the distorted region. When entering the distortion, the blade passage faces a positive pre-swirl, on the countary, when leavinging the distortion, the blade passage faces a negative pre-swirl, which increases its incidence angle and loading.
KW - Inlet Circumferential Distortion
KW - Numerical Simulation
KW - Transonic Rotor
UR - https://www.scopus.com/pages/publications/84886486640
U2 - 10.1109/ICDMA.2013.205
DO - 10.1109/ICDMA.2013.205
M3 - 会议稿件
AN - SCOPUS:84886486640
SN - 9780769550169
T3 - Proceedings - 2013 4th International Conference on Digital Manufacturing and Automation, ICDMA 2013
SP - 866
EP - 870
BT - Proceedings - 2013 4th International Conference on Digital Manufacturing and Automation, ICDMA 2013
T2 - 2013 4th International Conference on Digital Manufacturing and Automation, ICDMA 2013
Y2 - 29 June 2013 through 30 June 2013
ER -