B - Operations – Transporting – 23 – P
Patent
B - Operations, Transporting
23
P
B23P 6/00 (2006.01) F01D 5/00 (2006.01)
Patent
CA 2484438
A method facilitates repairing a gas turbine engine compressor blade airfoil (20). The method comprises removing titanium alloy material (61) from along leading and trailing edges (34 and 36) of the airfoil, and along a radially outer tip (40) of the airfoil to form respective leading edge, trailing edge, and tip cut-backs (62, 64, and 66) which each define cut-back depths (D1, D3, D2), and depositing titanium weld material (80)onto the leading edge, trailing edge, and tip cut-backs. The method also comprises removing at least some of the titanium weld bead material to obtain pre-desired finished dimensions for the leading and trailing edges, and radially outer tip.
Méthode qui facilite la réparation d'une surface portante de pale de compresseur de moteur de turbine à gaz (20). Elle comprend le retrait de l'alliage de titane (61) des bords d'attaque et de fuite (34 et 36) de la surface portante ainsi que du long de la pointe radiale extérieure (40) de la surface portante pour former les entailles du bord d'attaque, du bord de fuite et de la pointe (62, 64 et 66), qui définissent chacune des profondeurs d'entaille (d1, d3, d2), ainsi que pour le dépôt de titane de soudure (80) dans les entailles du bord d'attaque, du bord de fuite et de la pointe. La méthode comprend aussi le retrait d'au moins une partie des billes de titane de soudure pour obtenir les dimensions définitives souhaitées pour les bords d'attaque et de fuite et la pointe radiale extérieure.
Beneteau Douglas Paul
de Carvalho Raphael Rzepa
Stewart Matthew
Wilkins Melvin H.
Company General Electric
Craig Wilson And Company
LandOfFree
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