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GH220合金系仿苏—220合金,1980年由冶金工业部军工办和航空工业部科技局组织有关单位成立联合课题组进行攻关。 GH220合金在现今镍基变形高温合金中属于最高水平的合金之一,合金化程度高,强化相数量大,加工变形比较困难,相变规律复杂,又需采用特种弯曲晶界热处理工艺。该合金主要用作航空发动机涡轮叶片材料,短时工作温度达900～950℃,长时工作温度870～900°是国家急需的一个重要高温合金材料。研制中几乎没有任何工艺资料可以借鉴,研制工作有相当难度。
GH220 alloy imitation SU-220 alloy, in 1980 by the Ministry of Metallurgical Industry Military Office and the Ministry of Science and Technology Aviation Industry Organization unit set up a joint task force to tackle the problem. GH220 alloy in today’s nickel-based deformation superalloy one of the highest levels of alloying, a high degree of alloying, a large number of strengthening phase, processing deformation is more difficult, complex phase transition law, but also the use of special bending grain boundary heat treatment process. The alloy is mainly used as aeroengine turbine blade material, short-term operating temperature of 900 ~ 950 ℃, long-term operating temperature of 870 ~ 900 ° is an urgent need for a national high-temperature alloy material. There is almost no development of process information can learn from, research and development have considerable difficulty.