Turbulator configuration for cooling passages of an airfoil in a

Details Turbulator configuration for cooling passages of an airfoil in a Turbulator configuration for cooling passages of an airfoil in a

1997-01-03

1998-04-14

Kwon, John T.

Fluid reaction surfaces (i.e., impellers)

With heating, cooling or thermal insulation means

Changing state mass within or fluid flow through working...

415115, F04D 2958

Patent

active

057384932

ABSTRACT:
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.

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patent: 5611662 (1997-03-01), Cunha

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