Turbine Dovetail Slot Heat Shield

Abstract: Gas turbine engine turbine blade assembly (10) includes a hollow airfoil (16) joined to blade root (18), dovetail slot heat shield (40) bonded or attached to a bottom surface (37) of the root (18), and a shield outlet (93) from heat shield (40) open to inlet apertures (50) extending radially through a radially inner root end (35) of the root (18). Heat shield (40) may have body (88) with legs (92) extending upwardly from heat shield bottom (90), slanted open upstream end (100), and free ends (98) of the legs (92) longer than the heat shield bottom (90). Flanges (96) may be located along free ends (98) and bonded to bottom surface (37). Body (88), heat shield bottom (90) and/or the legs (92) may be rounded. Disk (30) includes a plurality of dovetail slots (29) formed in a rim (24), complimentary plurality of turbine blades (10) removably retained in dovetail slots (29) by the roots (18), slot bottoms (60) of the dovetail slots (29) extending circumferentially between disk posts (62) in rim (24). Heat shield bottoms (90) may be radially spaced apart the slot bottoms (60).

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