| 摘要 |
<p>A turbulator configuration is formed on an inner surface (36) 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 (62) extending therethrough. The turbulator configuration includes a plurality of spaced turbulator pairs (56A) 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 ( alpha 1) 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. <IMAGE> <IMAGE> <IMAGE></p> |
