Abstract: A liner for a composite blade of a gas turbine engine includes a metallic shoe, operable substantially to encase a blade root of a composite blade and defining an inner surface and an outer surface. The liner also includes a retention lug formed on the shoe and has inner and outer keys that project from opposed portions of the inner and outer surfaces. The keys engage corresponding recesses on a dovetail slot and a blade root to resist axial displacement of the composite blade.

Abstract: An aerofoil blade assembly having a rotor disc having a radially outer surface provided with an axial slot and a radially inner surface provided with a circumferential slot, wherein the lower region of the axial slot intersects the upper region of the circumferential slot; an aerofoil blade having a blade root which is received by the axial slot and which is provided with a locating slot which corresponds to the circumferential slot; a retention key which engages with the circumferential slot and the locating slot to restrict axial displacement of the aerofoil blade with respect to the rotor disc, the retention key being provided with a socket which, when the retention key is engaged in the circumferential slot and the locating slot, is substantially aligned with the axial slot.

Abstract: A liner 2 for a composite blade 40 of a gas turbine engine is disclosed. The liner comprises a metallic shoe 4, operable substantially to encase a blade root 42 of a composite blade 40 and defining an inner surface 17 and an outer surface 19. The liner 2 further comprises a retention lug 6 formed on the shoe 4 and comprising inner and outer keys 24, 22 which project from opposed portions of the inner and outer surfaces. The keys are operable to engage corresponding recesses on a dovetail slot and a blade root to resist axial displacement of the composite blade.

Abstract: An aerofoil blade assembly having a rotor disc having a radially outer surface provided with an axial slot and a radially inner surface provided with a circumferential slot, wherein the lower region of the axial slot intersects the upper region of the circumferential slot; an aerofoil blade having a blade root which is received by the axial slot and which is provided with a locating slot which corresponds to the circumferential slot; a retention key which engages with the circumferential slot and the locating slot to restrict axial displacement of the aerofoil blade with respect to the rotor disc, the retention key being provided with socket which, when the retention key is engaged in the circumferential slot and the locating slot, is substantially aligned with the axial slot.

Abstract: In combination a mount frame adapted to be attached to a vehicle and a snowplow assembly. The mount frame comprises a pair of detachable receivers which receive a pair of horns extending rearwardly from the snowplow assembly. The snowplow assembly comprises an A-frame, a trunnion and a lift frame. A blade is attached to the front of the A-frame. A pair of spaced stand assemblies, each including a latching mechanism, support the snowplow assembly when the mount frame is separated from the snowplow assembly. The latching mechanisms secure the snowplow assembly to the mount frame.