HYBRID ADDITIVE MANUFACTURING REPAIR METHOD
A repair method can comprise: machining a wall of the case to remove a damaged portion of the wall, the case including a metal alloy, the case originally formed by casting; arc welding an intermediate layer of a first material to a base surface formed from the machining to form a first portion of a repaired wall; and building up, via direct energy deposition, a remainder of the repaired wall with a second material.
1 . A method of repairing a case, the method comprising:
machining a wall of the case to remove a damaged portion of the wall, the case including a metal alloy, the case originally formed by casting;
arc welding an intermediate layer of a first material to a base surface formed from the machining to form a first portion of a repaired wall; and
building up, via direct energy deposition, a remainder of the repaired wall with a second material.
2 . The method of claim 1 , wherein the wall extends axially from a radial flange of the case.
3 . The method of claim 1 , wherein the arc welding is one of gas tungsten arc welding (“GTAW”), shield metal arc welding (“SMA”), plasma arc welding (“PAW”).
4 . The method of claim 1 , wherein a height ratio of the remainder of the repaired wall to the intermediate layer is between 20:1 and 2:1.
5 . The method of claim 1 , wherein the first material has a lower strength relative to the second material.
6 . The method of claim 1 , wherein a base material of the wall is the second material, and wherein the second material is different from the first material.
7 . The method of claim 6 , wherein the metal alloy comprises between 50% and 55% nickel, between 17% and 21% chromium, between 15% and 21% iron, between 4.75% and 5.5% niobium plus tantalum, between 2.8% and 3.3% molybdenum, between 0.65% and 1.15% titanium, between 0.2% and 0.8% aluminum, a maximum of 0.08% carbon, and nominal amounts (in weight percentage) of other elements.
8 . The method of claim 7 , wherein the first material of the intermediate layer comprises at least one of:
a first metal alloy including a first nominal composition of nickel fifty-eight percent (58%), chromium 20% to 23%, iron up to 5%, molybdenum between 8% to 10%, niobium (plus tantalum) between 3.15% to 4.15%,
a second metal alloy including a second nominal composition of nickel 63%, cobalt up to 2.5%, iron 6%, chromium 5%, molybdenum 25%, tungsten up to 1%, manganese up to 1%, silicon up to 1%, vanadium up to 0.6%, and carbon up to 0.12%, and
a third metal alloy including a third nominal composition of between 50% and 55% nickel, between 17% and 21% chromium, between 15% and 21% iron, between 4.75% and 5.5% niobium plus tantalum, between 2.8% and 3.3% molybdenum, between 0.65% and 1.15% titanium, between 0.2% and 0.8% aluminum, a maximum of 0.08% carbon, and nominal amounts (in weight percentage) of other elements.
9 . The method of claim 1 , wherein:
the wall includes a radially outer surface, and
the damaged portion of the wall includes a worn area in the radially outer surface.
10 . A method of repairing a flange of an aircraft component, the method comprising:
removing a damaged flange from the aircraft component, the aircraft component including a metal alloy, the aircraft component originally formed by casting;
arc welding an intermediate layer of a first material to a base surface formed from the removing, the intermediate layer forming a portion of a repaired flange; and
building up, via direct energy deposition, a remainder of the repaired flange with a second material to form a remaining portion of the repaired flange.
11 . The method of claim 10 , wherein the arc welding is one of gas tungsten arc welding (“GTAW”), shield metal arc welding (“SMA”), plasma arc welding (“PAW”).
12 . The method of claim 11 , wherein a height ratio of the remainder of the repaired flange to the intermediate layer of the repaired flange is between 20:1 and 2:1.
13 . The method of claim 10 , wherein the metal alloy comprises between 50% and 55% nickel, between 17% and 21% chromium, between 15% and 21% iron, between 4.75% and 5.5% niobium plus tantalum, between 2.8% and 3.3% molybdenum, between 0.65% and 1.15% titanium, between 0.2% and 0.8% aluminum, a maximum of 0.08% carbon, and nominal amounts (in weight percentage) of other elements.
14 . The method of claim 13 , wherein the first material of the intermediate layer comprises at least one of:
a first metal alloy including a nominal composition of nickel fifty-eight percent (58%), chromium 20% to 23%, iron up to 5%, molybdenum between 8% to 10%, niobium (plus tantalum) between 3.15% to 4.15%, or
a second metal alloy including a nominal composition of nickel 63%, cobalt up to 2.5%, iron 6%, chromium 5%, molybdenum 25%, tungsten up to 1%, manganese up to 1%, silicon up to 1%, vanadium up to 0.6%, and carbon up to 0.12%.
15 . The method of claim 13 , wherein the second material is different from the first material, and wherein the first material is a same material as the metal alloy.
16 . The method of claim 10 , wherein the first material has one of a lower strength or a same strength relative to the second material.
17 . A repaired cast component, comprising:
a wall defining an arcuate shape, the wall made of a base metal alloy, the wall originally formed by casting; and
a flange extending from the wall, the flange comprising an intermediate layer formed from a first metal alloy and a remainder portion formed from a second metal alloy, the second metal alloy different from the first metal alloy.
18 . The repaired cast component of claim 17 , wherein the base metal alloy comprises between 50% and 55% nickel, between 17% and 21% chromium, between 15% and 21% iron, between 4.75% and 5.5% niobium plus tantalum, between 2.8% and 3.3% molybdenum, between 0.65% and 1.15% titanium, between 0.2% and 0.8% aluminum, a maximum of 0.08% carbon, and nominal amounts (in weight percentage) of other elements.
19 . The repaired cast component of claim 18 , wherein the second metal alloy is a same metal as the base metal alloy.
20 . The repaired cast component of claim 19 , wherein the first metal alloy is at least one of:
a first nominal composition of nickel fifty-eight percent (58%), chromium 20% to 23%, iron up to 5%, molybdenum between 8% to 10%, niobium (plus tantalum) between 3.15% to 4.15%, or
a second nominal composition of nickel 63%, cobalt up to 2.5%, iron 6%, chromium 5%, molybdenum 25%, tungsten up to 1%, manganese up to 1%, silicon up to 1%, vanadium up to 0.6%, and carbon up to 0.12%.