The present paper shows the results of an experimental investigation on film cooling of a nozzle vane cascade with endwall contouring. In film cooled endwall the front area, especially close to the leading edge, is one of the most critical regions to be cooled; in case of a contoured endwall the thermal protection becomes even more difficult because of the endwall curvature effects. Two geometries with four rows of holes have been considered: a first one with cylindrical holes, the second one with fan-shaped holes. Compared to the former, the latter was expected to improve effectiveness levels. For both configurations tests have been carried out at low speed (M2is = 0.2) and low inlet turbulence intensity level, with coolant mass flow ratio varied within the 0.5-2.5% range. For each injection condition aerodynamic and thermal performance have been determined. Fan shaped holes provided a better thermal coverage compared to cylindrical ones nevertheless an increase in coolant consumption, but the front area cooling remained unsatisfactory.

(2009). Experimental Analysis of the Combining Effects of Endwall Contouring and Film Cooling through Shaped Holes [conference presentation - intervento a convegno]. Retrieved from http://hdl.handle.net/10446/23245

Experimental Analysis of the Combining Effects of Endwall Contouring and Film Cooling through Shaped Holes

BARIGOZZI, Giovanna;FRANCHINI, Giuseppe;PERDICHIZZI, Antonio Giovanni;RAVELLI, Silvia
2009-01-01

Abstract

The present paper shows the results of an experimental investigation on film cooling of a nozzle vane cascade with endwall contouring. In film cooled endwall the front area, especially close to the leading edge, is one of the most critical regions to be cooled; in case of a contoured endwall the thermal protection becomes even more difficult because of the endwall curvature effects. Two geometries with four rows of holes have been considered: a first one with cylindrical holes, the second one with fan-shaped holes. Compared to the former, the latter was expected to improve effectiveness levels. For both configurations tests have been carried out at low speed (M2is = 0.2) and low inlet turbulence intensity level, with coolant mass flow ratio varied within the 0.5-2.5% range. For each injection condition aerodynamic and thermal performance have been determined. Fan shaped holes provided a better thermal coverage compared to cylindrical ones nevertheless an increase in coolant consumption, but the front area cooling remained unsatisfactory.
2009
Barigozzi, Giovanna; Franchini, Giuseppe; Perdichizzi, Antonio Giovanni; Ravelli, Silvia
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Utilizza questo identificativo per citare o creare un link a questo documento: https://hdl.handle.net/10446/23245
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