Patent ID: 9482101
Filing Date: 2016-11-01
CPC Classification: F01D,F05D,Y02T

Claim Text:
1. A gas turbine engine component comprising: an airfoil extending radially from a root section to a tip section and comprising a trailing edge cooling passageway; a plurality of first flow dividers in the cooling passageway, the first flow dividers having a first longitudinal axis, wherein the first flow dividers are axially elongated oblong pedestals and each of the first flow dividers comprises an upstream end and a downstream end, and wherein the upstream end and the downstream end of each first flow divider are connected by two substantially parallel sides; at least one second flow divider in the cooling passageway between the plurality of first flow dividers and the tip section, the at least one second flow divider having a second longitudinal axis that is offset by a first angle with respect to the first longitudinal axis, wherein the at least one second flow divider comprises an upstream end and a downstream end, and wherein the upstream end and the downstream end are connected by two sides that are substantially straight, and wherein the radial thickness of the at least one second flow divider decreases from the upstream end to the downstream end; a third flow divider in the cooling passageway between the at least one second flow divider and the tip section, the third flow divider having a third longitudinal axis that is offset by a second angle with respect to the first longitudinal axis, wherein the second angle is different from the first angle.