Abstract: A turbine rotor disk assembly for an axial flow gas turbine engine includes a rotor disk (18) and a faceplate (22) axially engaged therewith by rotationally engaged securing means such as a pair of corresponding hooked members (42, 44). Disengagement of the faceplate (22) and the rotor disk (18) is prevented by the cooperation of an axially projecting tab (58), integral with the turbine blade, (20) and a corresponding faceplate recess (60).

Abstract: Apparatus for cooling the nozzle guide vanes in the turbine section of a gas turbine engine is disclosed. A plurality of guide vanes is cantilevered from the turbine case and extends radially inward across the path of working medium gases flowing through the turbine. A ring which is deformable in response to pressure forces is disposed between the vanes and the turbine case forming an annular chamber from which air is metered to the vanes during operation of the engine for cooling. In one embodiment platform cavities and airfoil cavities are alternately disposed between the vanes and the ring to isolate airfoil cooling air from platform cooling air.