US 7,509,736 B2
Process for repairing metallic pieces especially turbine blades of a gas turbine motor
Christian Boudereau, Moissy Cramayel (France); Michel Boulnois, Lieusaint (France); Hassan Boussaboun, Deuil la Barre (France); Charles Caruana, Asnieres (France); Jean-Marc Caux, Saint Brice (France); Francis Chareyre, Franconville (France); Gerard Defrocourt, Sannois (France); Patrick Herault, Saint Leu d'esserent (France); Clement Sampaio, Montmagny (France); and Jean-Jacques Varin, Pointoise (France)
Assigned to Snecma, Paris (France)
Filed on Oct. 08, 2004, as Appl. No. 10/960,704.
Claims priority of application No. 03 11885 (FR), filed on Oct. 10, 2003.
Prior Publication US 2005/0120555 A1, Jun. 09, 2005
Int. Cl. B23P 6/00 (2006.01)
U.S. Cl. 29—889.1  [29/402.05; 29/402.06; 29/402.07; 29/402.18; 29/402.19] 12 Claims
OG exemplary drawing
 
1. A process for repairing a metallic shroud of a gas turbine blade comprising an anti-wear layer of cobalt-based alloy over a metallic substrate, wherein said shroud has a leading edge and a trailing edge oriented transversely relative to a direction of flow of gas, the two edges being connected by two lateral edges that have a Z profile with two axial portions interconnected by a substantially transversal portion, said process comprising the steps of:
removing a portion of said anti-wear layer of cobalt-based alloy to a removal depth that is greater than a depth of wear of said anti-wear layer;
leaving a trace of said anti-wear layer of cobalt-based alloy to subsist above said metallic substrate, wherein said trace of said anti-wear layer extends at least in a re-entrant zone of the Z profile; and
applying drops of said cobalt-based alloy to contact said trace thereby soldering a new layer of anti-wear material of cobalt-based alloy on said trace of said anti-wear layer,
wherein said removing step is performed such that said trace has a shape that ensures that said drops of the cobalt-based alloy are not brought into a zone free of said trace of cobalt-based alloy.