Turbulator configuration for cooling passages of an airfoil in a gas turbine engine

摘要

A turbulator configuration formed on an inner surface of at least one wall of a cooling passage for a rotor blade in a gas turbine engine is disclosed, where the cooling passage has an upstream end, a downstream end, and a longitudinal axis therethrough. The turbulator configuration includes a first set of longitudinally spaced turbulators having a specified height and length for tripping a thermal boundary layer along the cooling passage wall to enhance heat transfer between the coolant and the wall, as well as a second set of longitudinally spaced turbulators having a specified height and length for generating turbulence in a core flow region of the cooling passage to reduce the thickness of the thermal boundary layer downstream therefrom.