Most of the energy loss in turbine nozzles is associated with 3-D secondary flows that result from the interaction between the surface boundary layers and the nozzle row with its associated pressure field. Three alternative nozzles with differences in their designs to control secondary flows are studied. These chosen nozzle guide vanes are representative of the current generation of high hub-tip ratio aero engine nozzles. A computational analysis of all three nozzles is presented including predictions from three alternative viscous, 3-D methods. These detailed measurements and predictions demonstrate the influence of the vane geometries on the magnitude and the distribution of the secondary losses.
Investigation of Secondary Flows in Nozzle Guide Vanes
1989
14 pages
Report
No indication
English
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