Abstract: An apparatus for manufacturing a hollow turbomachine blade made from a titanium alloy of the TA6V type includes a hot twisting step in which an element of the blade is twisted progressively at a temperature above 700° C. by a plurality of bars which are rotated about the twist axis and act on collars previously fixed to the element, the distribution and number of collars being determined according to the desired twist to be imparted and such as to obtain a linear twist development between each collar.

Abstract: A process for joining a base for an airfoil to a disk for an integrally bladed rotor stage in a gas turbine engine includes providing a disk having a radially outer rim with a slot defined therein by a recessed surface, and further includes providing a base having a longitudinally extending root portion facing opposite a longitudinally extending support portion for supporting the airfoil. The root portion has a root surface and the support portion has an outer surface. The process further includes bringing the root surface of the root portion into contact with the recessed surface bounding the slot, applying pressure and relative movement between the base and the rim to achieve during welding, substantial contiguity between the root surface and the recessed surface over the area of the recessed surface, resulting in a substantially continuous linear friction weld between the base and the rim.