Patent ID: 6602047
Filing Date: 2003-08-05
Classification: F01D,F05D,Y02T

Abstract:
A method for cooling a turbine nozzle for a gas turbine engine, the nozzle including an airfoil, said method comprising:providing an airfoil including a first sidewall and a second sidewall connected at a leading edge and a trailing edge such that a cavity is defined therebetween, the airfoil also including a plurality of pins extending between the first and second sidewalls, and at least one row of turbulators, the first sidewall including a plurality of slots in flow communication with the airfoil cavity and extending through the first sidewall towards the trailing of the airfoil; and channeling cooling air into the airfoil cavity such that the airflow is routed through the pins and then through the turbulators before exiting the airfoil through the first sidewall slots.