Abstract: In a turbojet engine of the kind having a fan, the face of the radially outer tip of each rotor blade of the fan has a radiussed profile centered at a point R situated in a position displaced on the concavely curved side of the blade relative to its radial axis and beyond the rotational axis of the engine relative to the blade.

Abstract: A turbomachine rotor disc assembly includes a rotor disc having a plurality of blade-root grooves in its periphery, each two adjacent grooves defining a lobe lug between them. Rotor blades each include an aerofoil portion, a root portion, a platform defining the radially inner boundary of the aerofoil portion, and a stilt portion interconnecting the radially inner face of the platform and the root portion, a free space being defined between each adjacent pair of blades. The angular clearance of each blade in its groove is limited by wedges operative between adjacent blades on the stilts thereof and connecting members carrying the wedges secured to the rotor disc and capable of transmitting shock loads and distributing resultant forces over an adjacent sector of the rotor. The wedges are so dimensioned in relation to the dimensions of the stilts of adjacent blades that the angular clearance is limited to the permissible angular clearance of each blade during auto-rotation of the rotor.