Patent ID: 6969230
Filing Date: 2005-11-29
Classification: F01D,F05D,Y02T

Abstract:
1. A gas turbine engine airfoil comprising: pressure and suction sidewalls extending longitudinally in airfoil span between a root and a tip, and chordally between opposite leading and trailing edges, and spaced laterally apart therebetween to define an internal cooling circuit; a plurality of venturi slots terminating adjacent said trailing edge and commencing inside said airfoil in flow communication with said cooling circuit; each of said venturi slots including in serial flow communication a flared inlet, a converging portion adjoining said inlet, a throat of minimum flow area adjoining said converging portion, a diverging portion adjoining said throat, and an outlet adjoining said diverging portion and exposed adjacent said trailing edge for discharging said coolant; and said slot converging portion being comparable in chordal length to said throat and tapering in radial span substantially linearly from said flared inlet to said throat.