Patent ID: 8366393
Filing Date: 2013-02-05
Classification: F01D,F05D,Y10T

Abstract:
1. A rotor blade for a gas turbine engine, the blade comprising: an airfoil portion containing at least one internal conduit for the transport of cooling air therethrough, the at least one conduit extending to an end of the airfoil portion, a shroud at the end of the airfoil portion for sealing the blade, in use, to a facing stationary portion of the engine, and a fillet portion which joins said end to the shroud, the fillet portion easing the transition from the outer surface of the airfoil portion to the outer surface of the shroud; wherein the fillet portion contains a cavity which extends from the at least one conduit and expands laterally relative to the at least one conduit, such that the area of the cavity on a cross-section through the fillet portion perpendicular to the radial direction of the engine and at an expanding part of the cavity is greater than the area of the conduit, or the combined areas of the conduits, on a parallel cross-section at the end of the airfoil portion, wherein the shroud further has a plurality of first passages through which cooling air from the cavity flows to respective exit holes on the outer surfaces of the shroud, and wherein the shroud further has at least one or more recess at the outer surface thereof, at least a portion of the first passage having their exit holes at the at least one recess, and wherein a recess is positioned at a downstream edge portion of the shroud.