论文部分内容阅读
GH220合金是一种时效硬化型的难变形高温镍基合金。作航空发动机涡轮叶片之用。使用温度为900～950℃,使用总寿命达1200h 合金采用1220℃×4h,空冷;1050℃×4h,空冷;950℃×2h,空冷(即直晶热处理工艺)与1220℃×4h,缓冷;1050℃×4h,空冷;950℃×2h,空冷(即弯晶热处理工艺)后,再经900℃长期时效处理,合金析出少量针状TCP(μ)相。试验结果表明,合金经900℃×1200h处理,析出少量μ相,但对性能衰减无直接影响。弯晶热处理工艺大大地延迟针状相的析出。
GH220 alloy is a kind of aging hardenable high temperature nickel-based alloys. Used as aeroengine turbine blades. The temperature of 900 ~ 950 ℃, the use of the total life of 1200h alloy with 1220 ℃ × 4h, air cooling; 1050 ℃ × 4h, air cooling; 950 ℃ × 2h, air cooling (ie straight crystal heat treatment process) and 1220 ℃ × 4h, ; 1050 ℃ × 4h, air cooling; 950 ℃ × 2h, air cooling (ie, bending heat treatment process), and then long-term aging treatment at 900 ℃, the alloy precipitated a small needle TCP (μ) phase. The experimental results show that the alloy precipitates a small amount of μ phase after being treated at 900 ℃ for 1200h, but has no direct effect on the performance degradation. Bending heat treatment process greatly delayed the precipitation of acicular phase.