Patent ID: 7114339
Filing Date: 2006-10-03
Classification: F01D,F02C,F05D,Y02T

Abstract:
1. A gas turbine engine comprising: a compressor section; a combustion section downstream of the compressor section; a turbine section having a longitudinal axis downstream of the combustion section; an axial flow plenum extending through the engine, the axial flow plenum having at least one outlet fluidically coupled to the turbine section; at least one fluid flow directional modifier disposed proximate the axial flow plenum; and wherein said at least one fluid flow directional modifier extends directly from a wall forming a trailing edge of a vane and is in the form of a turning foil with an arcuate surface along a radial direction that encourages parasitic leakage air flowing radially outwardly to be turned so as to be flowing substantially parallel to the gas flow path at the trailing edge of the vane.