TY - JOUR
T1 - Vortex-lift mechanism in axial turbomachinery with periodically pitched stators
AU - Du, Lin
AU - Sun, Xiaofeng
AU - Yang, Vigor
N1 - Funding Information:
Acknowledgments The financial support of the National Natural Science Foundation of China (grants 51236001 and 51076006) and the 973 Program (grant 2012CB720200) are gratefully acknowledged.
Publisher Copyright:
© 2012 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.
PY - 2016
Y1 - 2016
N2 - Conventional aerodynamic theory of lift is based on the Kutta-Joukowski condition, in which the lift and drag coefficients are predicted basedon the assumption that flow is attached and steady-state. Recent researchoninsect flight indicates, however, that the unsteady motion of a wing can generate much higher unsteady aerodynamic force through the flow induced by the shedding vortices. In the present work, therefore, we propose a novel type of stage consisting of rotor and periodically pitched stator to take advantage of unsteady vortex lift. The numerical results suggest that the flowfield around the leading and trailing edges of the blades are substantially modified by the interactions between the rotor and pitchingstator.Several transientlift peakscanbegenerated foreach period.Ifanappropriate pitchingphaseis chosen for the stator, stage performance can be improved through unsteady lift mechanism effects. Copyright
AB - Conventional aerodynamic theory of lift is based on the Kutta-Joukowski condition, in which the lift and drag coefficients are predicted basedon the assumption that flow is attached and steady-state. Recent researchoninsect flight indicates, however, that the unsteady motion of a wing can generate much higher unsteady aerodynamic force through the flow induced by the shedding vortices. In the present work, therefore, we propose a novel type of stage consisting of rotor and periodically pitched stator to take advantage of unsteady vortex lift. The numerical results suggest that the flowfield around the leading and trailing edges of the blades are substantially modified by the interactions between the rotor and pitchingstator.Several transientlift peakscanbegenerated foreach period.Ifanappropriate pitchingphaseis chosen for the stator, stage performance can be improved through unsteady lift mechanism effects. Copyright
UR - https://www.scopus.com/pages/publications/84962783975
UR - https://www.scopus.com/pages/publications/84962783975#tab=citedBy
U2 - 10.2514/1.B35859
DO - 10.2514/1.B35859
M3 - Article
AN - SCOPUS:84962783975
SN - 0748-4658
VL - 32
SP - 486
EP - 499
JO - Journal of Propulsion and Power
JF - Journal of Propulsion and Power
IS - 2
ER -