Stress Relieving Slots for Turbine Vane Ring

摘要

A turbine vane ring (10) has a radially outer and inner annular shrouds (12,11) defining therebetween an annular gaspath. Circumferentially spaced-apart airfoil vanes (13) extend radially across the gaspath between the outer and the inner shrouds (12,11). The radially outer shroud (12) has a circumferentially continuous cylindrical wall (14) extending axially from a leading edge (18) to a trailing edge. A set of circumferentially distributed stress relieving slots (17) is defined in the leading edge (18) of the cylindrical wall (14) at locations adjacent to the leading edge of at least some of said airfoil vanes (13). The stress relieving slots (17) extend radially through the cylindrical wall (14) from the radially inner surface to the opposed radially outer surface thereof.