Turbulator configuration for cooling passages or rotor blade in

Details Turbulator configuration for cooling passages or rotor blade in Turbulator configuration for cooling passages or rotor blade in

1997-01-03

1998-08-25

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...

416 97R, F04D 2958

Patent

active

057977267

ABSTRACT:
A turbulator configuration is formed on an inner surface of one or more walls defining a cooling passage in a rotor blade of a gas turbine engine, where the cooling passage has a centerline extending therethrough. The turbulator configuration includes a plurality of spaced turbulator pairs oriented with respect to the centerline so that the direction of a boundary layer flow of the coolant adjacent the cooling passage inner surface is consistent with a pair of counter-rotating flow circulations created by Coriolis forces on the coolant flowing into and through the cooling passage when the rotor blade is rotated, whereby heat transfer between the coolant and the wall is enhanced. The turbulator pairs are angled either toward or away from the centerline for leading and trailing walls of the cooling passage depending upon whether the coolant is flowing either radially outward or radially inward.

REFERENCES:
patent: 4416585 (1983-11-01), Abdel-Messeh
patent: 4514144 (1985-04-01), Lee
patent: 5156526 (1992-10-01), Lee et al.
patent: 5165852 (1992-11-01), Lee et al.
patent: 5423608 (1995-06-01), Chyou et al.
patent: 5536143 (1996-07-01), Jacala et al.

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