Abstract:
A method of repairing a braze joint (16) and the resulting joint includes removing an unsuitable portion (20) of a first joining material (18) in a joint (16) between a first member (12) and a second member (14) of an aerospace assembly (10) and cleaning the joint (16). A stripping solution is used to remove the unsuitable portion (20) of the first joining material (18). A first cleaning solution is used to clean the joint (16), and the joint (16) is further cleaned using a second cleaning solution. During a rebrazing step, a second joining material (60) moves into a void left by the removed unsuitable portion (20) from the removal step to form a new joint between the first member (12) and the second member (14) that includes the remaining first joining material (18) and the second joining material (60).
Abstract:
In accordance with a first embodiment of the present invention, a nickel alloy welding wire is made from a material comprising from about 4.75 to 5.25 wt% chromium, from about 5.5 to 5.8 wt% aluminum, from about 5.6 to 6.2 wt% tungsten, from about 8.0 to 8.3 wt% tantalum, from about 1.7 to 2.1 wt% molybdenum, from about 9.5 to 10.5 wt% cobalt, from about 2.8 to 3.2 wt% rhenium, from about 0.07 to 0.30 wt% carbon, from about 0.02 to 0.04 wt% boron, from about 0.08 to 0.12 wt% zirconium, from about 0.08 to 0.12 wt% yttrium, from about 1.0 to 1.5 wt% hafnium, and the balance nickel. In a second embodiment of the present invention, a nickel alloy welding wire is made from a material comprising from about 4.75 to 5.25 wt% chromium, from about 5.5 to 5.8 wt% aluminum, from about 5.6 to 6.2 wt% tungsten, from about 8.0 to 9.0 wt% tantalum, from about 1.7 to 2.1 wt% molybdenum, from about 9.5 to 10.5 wt% cobalt, from about 2.8 to 3.2 wt% rhenium, from about 0.18 to 0.30 wt% carbon, from about 0.02 to 0.04 wt% boron, from about 0.08 to 0.12 wt% zirconium, from about 0.08 to 0.12 wt% yttrium, from about 1.0 to 1.5 wt% hafnium, and the balance nickel.
Abstract:
A method of repairing a braze joint (16) and the resulting joint includes removing an unsuitable portion (20) of a first joining material (18) in a joint (16) between a first member (12) and a second member (14) of an aerospace assembly (10) and cleaning the joint (16). A stripping solution is used to remove the unsuitable portion (20) of the first joining material (18). A first cleaning solution is used to clean the joint (16), and the joint (16) is further cleaned using a second cleaning solution. During a rebrazing step, a second joining material (60) moves into a void left by the removed unsuitable portion (20) from the removal step to form a new joint between the first member (12) and the second member (14) that includes the remaining first joining material (18) and the second joining material (60).
Abstract:
A method of homogeneously welding a superalloy which includes preheatin g the superalloy prior to welding and allowing it to cool prior to welding. Th e alloy is then welded, cooled to room temperature and then heated to stress relieve.