IGTC-17 Secondary Flow Development Downstream of a Transonic Cascade(Session A-5 AERODYNAMICS V (Turbomachinery))

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Results of an experimental investigation of a 3-D flow field at the exit of a linear turbine cascade are presented. The blade has an aspect ratio h/c=1.05 and a turning angle Δβ'=83.4. Tests were performed for two outlet Mach numbers M2 is=0.5 and 1.02, in order to show the different behaviour of secondary flow development due to compressibility effects. Detailed flow measurements, using a five hole miniaturized probe, were carried out at four different planes downstream of trailing edge. The results are presented in terms of loss coefficient contour plots and secondary velocity vector distribution from which it is possible to follow the evolution of passage, shed, and corner vortices. These plots revealed that, as Mach number increases, passage vortex moves closer the endwall. Going down-stream of the cascade both passage and shed vortices were found to migrate toward the midspan. Pitchwise mass average distribution of losses and flow angles showed generally decreasing losses together with clear reduction of flow angle deviations (overturning and underturning), as Mach number increases.
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