CM 186 LC alloy, a second generation Re-containing directionally solidified (DS), columnar grain superalloy, was developed with both component producibility and economic objectives particularly in mind. As vane component design trends toward increasing complex cooling configurations — with thin walls [.020″ (.5mm)], large overhanging integral shrouds and wide chord 3-d computer design airfoils — they can be difficult and expensive to manufacture as single crystals (SX), due to problems arising with grain and recrystalization. For this reason, many turbine designers consider high strength DS alloys a viable alternative to SX. An alloy, castibility, therefore, becomes crucial to manufacturing success. To this end, the CM 186 LC Ds castibility is confirmed to be outstanding. Since the alloy is used in the as-cast and double-aged condition, recrystalization concerns are significantly reduced as well as associated process costs.
The CM 186 LC alloy from Cannon Muskegon develops DS longitudinal creep-rupture properties equivalent to first generation single crystal alloys CMSX-2® and CMSX-3® up to 1800°F (982°C). Strength at higher temperatures lies between CMSX-2/3 alloys and the solution treated DS alloy CM 247 LC®. CM 186 LC alloy can be manufactured from virgin CMSX -2, -3 or -4 alloy foundry revert blends thereby favorably impacting cost of manufacture.CM 186 LC alloy has been successfully scaled to 8000 lb. (3630 kg) production size heats.
The alloy is in field application for DS turbine blades for the EGT (Alstrom) industrial engine. The alloy is also in flight engine service as both DS and single crystal vane segments.
|Density 0.314 lbs./cu in (8.70 kg/dm3).|
|Excellent DS Castibility. Above average resistance to grain boundary cracking in complex cored, thin wall turbine airfoils.|
|Oxidation, Type 1 hot corrosion (sulphidation) and coating performance as measured through cyclic burner rig testing, is similar to MAR M 247 alloy.|
|Good DS transverse stress-rupture ductility is maintained through all temperature extremes, even in the normal ductility trough region for this category material.|
|Satisfactory phase stability following 13,400 hr. stressed exposure at 1800°F (982°C) and 5000 hr. stressed exposure at 2000°F (1093°C) is apparent.|
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