... ′ 35 deg, 45 deg Lateral angle F 45 deg, 60 deg, 90 deg Area ratio A R 1.8, 3.71, 5.0 Pitch to diameter ratio P / D 5.0, 8.0 boundary layers coolants cooling engines flow infrared imaging Film cooling is state-of-the-art technology...

.... They are, however, confined to steady flows. In the present work, a new approach to conjugate analysis for periodic unsteady flows is proposed and demonstrated. First, a simple model analysis is carried out to quantify the huge disparity in time scales between convection and conduction, and the implications...

...Tobias Brandvik; Graham Pullan A new three-dimensional Navier–Stokes solver for flows in turbomachines has been developed. The new solver is based on the latest version of the Denton codes but has been implemented to run on graphics processing units (GPUs) instead of the traditional central...

...Aaron W. Costall; Robert M. McDavid; Ricardo F. Martinez-Botas; Nicholas C. Baines The pulsating nature of gas flow within the exhaust manifold of an internal combustion engine is not well captured by the quasi-steady techniques typically employed by cycle simulation programs for turbocharger...

...Jason A. Bourgeois; Robert J. Martinuzzi; Eric Savory; Chao Zhang; Douglas A. Roberts The accurate prediction of mean flow fields with high degrees of curvature, adverse pressure gradients, and three-dimensional turbulent boundary layers typically present in centrifugal compressor stages...

...Lesley M. Wright; Sarah A. Blake; Je-Chin Han An experimental investigation to obtain detailed film cooling effectiveness distributions on a cooled turbine blade platform within a linear cascade has been completed. The Reynolds number of the freestream flow is 3.1 × 10 5 , and the platform has...

...J. Schlienger; A. I. Kalfas; R. S. Abhari This paper presents time-resolved flow field measurements at the exit of the first rotor blade row of a two stage shrouded axial turbine. The observed unsteady interaction mechanism between the secondary flow vortices, the rotor wake and the adjacent...

... wind tunnel with a single stage turbine annular cascade was used. The turbine stage is composed of sixteen guide plates and blades. The chord length of blade is 150 mm and the mean tip clearance is about 2.5% of the blade chord. The tested Reynolds number based on inlet flow velocity and blade chord...

... are generated by the leakage flow across the shroud clearance. Generally the related losses can be grouped into losses of the leakage flow itself and losses caused by the interaction with the main flow in subsequent airfoil rows. In order to reduce the impact of the leakage flow and shroud design related losses...