Patent ID: 6129515
Filing Date: 2000-10-10
Classification: F01D,Y02T

Abstract:
For an airfoil of a turbine blade for a gas turbine engine being driven by the engine's working gases, said airfoil having internal passages for receiving coolant in the airfoil, said airfoil including pressure wall means for defining a pressure surface, a suction wall means defining a suction surface, a trailing edge formed at the spanwise edge of said pressure wall means and the spanwise edge of said suction wall means, at least one coolant passage for discharging coolant through an opening in said trailing edge, spaced chambers disposed in series in said coolant passage having progressively lower pressures, means for attaining film cooling effectiveness including a film cooling hole through said pressure wall means interconnecting the upstream chamber of said series connected chambers and an interconnecting passage interconnecting the downstream chamber and said film cooling hole of said series connected chambers, whereby the lower pressure in said downstream chamber creates a suction in a film cooling hole for adhering said film of coolant discharging through said cooling hole to minimize boundary layer mixing of said coolant and said gases over the outer surface of said trailing edge.