METHOD FOR FRICTION WELDING A BLADE ONTO A TURBINE ENGINE ROTOR DISC AND CORRESPONDING INTEGRAL BLADE DISC Russian patent published in 2018 - IPC B23K20/12 F01D5/34 B23P15/04 

FIELD: instrument engineering.

SUBSTANCE: invention can be used in the manufacture of a rotor disk of a gas turbine engine. Rotor disk comprises, on its outer peripheral part, contact protrusion (18), having a front and a back edge, onto which blade (32) is to be welded. Abutments (24) are mounted on said edges of the protrusion. Before welding by friction, the abutments are rigidly connected to the contact protrusion. In the welding process, weld seams (28) between the stops and the protrusion are pushed out, at least, partly into metal rollers (34), which are removed after welding. Welds (28) have depth (e) or a radial dimension with respect to the longitudinal axis of the disc, less or equal than half of the total thickness (E) of the metal, consumed during friction welding. Total thickness (E) is equal to the total thickness of feather (32) consumed in the process of welding by metal friction and metal of the contact projection (18).

EFFECT: due to the fact that the melted and heat-stressed zone, having a different structure and lower hardness, extruded into the rollers (grat), it does not affect the finished rotor disk.

9 cl, 9 dwg