The present numerical study deals with the steady and unsteady aerodynamics of an airfoil in a cascade with oscillating neighboring blades. The motivation for the study arises from aeroelastic studies of turbomachinery blades, where the unsteady forces acting on a blade due to different sources is examined. In order to identify the root cause of the various phenomena affecting the aeroelastic stability, it is necessary to observe the effect of only one source of disturbance and isolate the others. The cascade comprises of five blades with zero stagger and low incidence. The two adjacent blades to central one are oscillated with a fixed frequency and phase difference, with the rest of the blades remaining stationary, covering a range of frequencies and phase difference angles. The primary objective is to look at the variation of global parameters on central blade with reduced frequency. The moment and drag are estimated numerically and compared with experimental results which shows good agreement. The hysteresis loops of lift and moment coefficient with angular displacement are used to understand the effect of reduced frequency. A laminar separation bubble is observed to be formed during part of the oscillation cycle and its size is related to the unsteady forces on the blade. The behavior is also a function of reduced frequency to some extent. Such an understanding of the effect of oscillating blades in a blade row is essential for the modeling of the aerodynamic forces in an aeroelastic problem.
Numerical Study of Effect of Adjacent Blades Oscillation in a Compressor Cascade
Lect.Notes Mechanical Engineering
Design and Development of Aerospace Vehicles and Propulsion Systems ; Kapitel : 5 ; 59-74
2021-03-19
16 pages
Aufsatz/Kapitel (Buch)
Elektronische Ressource
Englisch
Experimental Study on Linear Compressor Cascade with Three-Dimensional Blade Oscillation
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