Patent ID: 8807944
Filing Date: 2014-08-19
Classification: F01D,F05D,Y02T

Abstract:
1. A fluid-cooled turbomachine airfoil component adapted for use in a hot gas path of a turbomachine, the airfoil component comprising: an airfoil portion having a span-wise direction delimited by an airfoil root and an airfoil tip, a chord-wise direction delimited by a leading edge and a trailing edge, and a thickness-wise direction delimited by concave and convex surfaces formed by walls that extend between the leading and trailing edges; a chamber within the airfoil portion; a first passage within the airfoil portion and adapted to fluidically connect the chamber to the airfoil root and a cooling fluid that enters the airfoil portion through the airfoil root; a second passage within the airfoil portion between the chamber and the airfoil tip thereof and adapted to fluidically connect the chamber to a first cooling hole located at a surface of the airfoil portion; and a porous and permeable foam member within the chamber; wherein the chamber is located relative to the first and second passages so as to be offset in the chord-wise direction toward the trailing edge of the airfoil portion so that the chamber is closer to the trailing edge than the first and second passages and the cooling fluid entering the airfoil portion through the first passage enters the chamber and is diverted by the foam member in the chord-wise direction toward the trailing edge before recirculating in the chord-wise direction toward the leading edge and exiting the airfoil portion through the first cooling hole.