These proceedings contain the 24 papers presented at the meeting on secondary flows in turbomachines. The meeting was arranged in the following sessions: Basic flow phenomena (6); Experimental results (5); Three-dimensional computation and comparison with experiments (5); Tip clearance flows (4); and Secondary flow effects on heat transfer (4). The specialists' meeting offered a forum for experts to discuss computational and experimental methods and results for secondary flow in cascades, compressors and turbines. CFD was found to be an adequate tool to represent qualitative phenomena, but on the accuracy of predicting losses and exit angles there was some disagreement. Many papers dealt with experimental investigations which are obviously essential for evaluating secondary flow models. Keywords: Three dimensional flow computations; Cascade structures; Axial flow compressors; Airfoils; Turbulent flow/mixing; Nozzle guide vanes; Transonic nozzles; Aspect ratio; Centrifugal impellers; Radial compressors; Blade tips; Turbine blades; Cascades fluid dynamics; Compressors; End wall flow; Computational fluid dynamics; Tip leakage flow; Secondary flow; Turbine guide vanes.

An investigation of secondary-flow loss cores originating in turbine nozzle blade passages was conducted by means of flow visualization studies and detailed flow measurements. The degree of which blade surface velocity profiles affect the magnitude and concentration of loss cores was investigated by comparing three nozzle blade configurations.

Flow-visualization techniques are employed to ascertain the streamline patterns of the nonpotential, secondary flows in the boundary layers of cascades, thereby providing a basis for more extended analyses in turbomachines. The three-dimensional deflection of the end-wall boundary layer results in the formation of a vortex well up in each cascade passage. The size and tightness of the vortex generated depend upon the main flow turning in the cascade passage. Once formed, a vortex resists turning in subsequent blade rows. This results in unfavorable angles of attack and possible flow disturbances on the pressure surfaces of subsequent blade rows when the vortices impinge on these surfaces.

An introduction to the theory and engineering practice that underpins the component design and analysis of radial flow turbocompressors. Drawing upon an extensive theoretical background and years of practical experience, the authors provide descriptions of applications, concepts, component design, analysis tools, performance maps, flow stability, and structural integrity, with illustrative examples. Features wide coverage of all types of radial compressor over many applications unified by the consistent use of dimensional analysis. Discusses the methods needed to analyse the performance, flow, and mechanical integrity that underpin the design of efficient centrifugal compressors with good flow range and stability. Includes explanation of the design of all radial compressor components, including inlet guide vanes, impellers, diffusers, volutes, return channels, de-swirl vanes and side-streams. Suitable as a reference for advanced students of turbomachinery, and a perfect tool for practising mechanical and aerospace engineers already within the field and those just entering it.