A two-dimensional unsteady analysis for transonic and supersonic cascade flows
Abstract
A mathematical model based on the two-dimensional unsteady full potential equation has been developed to predict the unsteady response of cascade flows at subsonic, transonic, and supersonic speeds. A time-marching algorithm based on a quasi-Newton-iteration technique is employed in this analysis. A time sheared scheme is used to calculate non-zero interblade phase angle oscillation cases. Multiple-passage calculations are needed if the interblade time lag is large. Contrary to the classical linear theory, the effects of blade shape, flow incidence angle, cascade geometries, and presence of shock wave are fully considered. The validity and accuracy of the present analysis has been demonstrated by comparison to available experimental data and other theoretical analyses over wide flow ranges for various cascade configurations. The mathematical model and procedures adopted in the present analysis can be applied to turbomachinery flutter analysis.
Degree
Ph.D.
Advisors
Williams, Purdue University.
Subject Area
Aerospace materials
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