Patent ID: 8864452

Claim:
A flow directing member for a gas turbine engine, the flow directing member including a platform supported on a rotor and comprising a radially facing endwall and opposed first and second axially facing axial surfaces extending radially inwardly from respective junctions with the endwall, the flow directing member further including an airfoil extending radially outwardly from the endwall and a fluid flow directing feature, the fluid flow directing feature comprising: a first groove extending axially into the first axial surface comprising a forward axial face, the first groove comprising: a radially inner groove end; a radially outer groove end spaced in a radial direction from the inner groove end; a first groove wall extending from the inner groove end to the outer groove end; a second groove wall opposed from the first groove wall and extending from the inner groove end to the outer groove end; and the outer groove end defining an axially extending notch in the junction between the first axial surface and the endwall and forming an opening in the endwall for directing a cooling fluid to the endwall; and a second groove extending axially into the second axial surface comprising an aft axial face, the second groove comprising: a radially inner groove end; a radially outer groove end spaced in the radial direction from the inner groove end; and wherein the outer groove end defines an axially extending notch in the junction between the second axial surface and the endwall and forming an opening in the endwall for directing a cooling fluid to the endwall.