Secondary Flows in a Transonic Cascade: Comparison Between Experimental and Numerical Results

[+] Author and Article Information
F. Bassi

Ist. di Macchine, Universitá di Catania, 95125 Catania, Italy

C. Osnaghi

Dip. di Energetica, Politecnico di Milano, 20133 Milano, Italy

A. Perdichizzi

Dip. di Ingegneria Meccanica, Universitá di Brescia, 25060 Brescia, Italy

M. Savini

CNPM - CNR, 20068 Peschiera Borromeo (MI), Italy

J. Fluids Eng 111(4), 369-377 (Dec 01, 1989) (9 pages) doi:10.1115/1.3243655 History: Received September 20, 1988; Online October 26, 2009


The paper presents a comparison between numerical results and experimental data about the secondary flow development in a linear transonic turbine cascade. Computations are carried out by using a three-dimensional inviscid Euler code, based on a Runge-Kutta explicit finite volume method. The experimental inlet total pressure distribution is imposed as inlet boundary condition to simulate the incoming endwall boundary layer. The comparison is made in four planes downstream of the cascade where detailed experimental data obtained in a transonic wind tunnel are available. For each of these planes secondary velocities and streamwise vorticity contour plots are presented and discussed. Moreover pitchwise mass averaged flow angle distributions showing overturning and underturning regions are shown. The comparison shows that an Euler code can predict the essential features of secondary flow phenomena like passage vortex location and intensity but a certain disagreement is found in the overturning and underturning angles evaluation. Numerical results also allow for the investigation of the development of secondary flows inside the blade channel. The investigation is carried out for three different Mach numbers: M2is = 0.5, 1.02, 1.38, in order to show the influence of compressibility on the flow vortex structure.

Copyright © 1989 by ASME
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