CPC F01D 5/187 (2013.01) [F01D 5/30 (2013.01); F01D 5/188 (2013.01); F05D 2230/21 (2013.01); F05D 2230/31 (2013.01); F05D 2240/127 (2013.01); F05D 2250/15 (2013.01); F05D 2250/25 (2013.01); F05D 2260/2212 (2013.01); Y02T 50/60 (2013.01)] | 14 Claims |
1. A turbine vane for a turbine engine such as a turboprop or a turbojet engine, said vane comprising a vane root supporting a blade, said vane including at least one air-circulation duct for cooling the vane during operation, said duct including, at the vane root, intake portions for collecting cooling air, said intake portions extending away from a lower surface of the vane root opposite to the blade, wherein at least one of said intake portions is provided with a helical element, having a base located at the lower surface of the vane root and extending into the vane root for swirling the cooling air in the at least one of said intake portions in order to improve the cooling efficiency thereof, wherein a calibrated plate is fixed to the lower surface of the vane root, said calibrated plate comprising holes for adjusting a rate of an intake air flow in each duct, wherein the helical element and the calibrated plate are a one-piece unitary element, wherein the helical element has a height that is twenty percent of a height of the intake portion that the helical element is disposed within.
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