The invention provides a low cost, high strength and fully
oxidation resistance third generation single crystal high-temperature
alloy. The high-temperature
alloy is mainly suitable for aircraft engine blade materials used at the temperature of 1100 DEG C or above. The
alloy is prepared from the chemical components in percentage by weight: 3-5% of Cr, 5-12% of Co, 6-8% of W, 0.1-2% of Mo, 4.5-5.5%of Re, 5.5-6.5% of Al, 6-10% of Ta, 0-0.6% of Nb, 0-0.2% of Hf, 0-0.05% of Y, 0-0.04% of C, and the balance of Ni. A preparation method comprises the steps that
single crystal blades or test rods areprepared within a
temperature gradient range of a
single crystal growth furnace being 40 K / cm-80 K / cm, at a
casting temperature of 1500-1550 DEG C, under the condition that a mould shell temperatureis consistent with the
casting temperature, and within the growth rate range of 4-8 mm / min. Then after
solid solution homogenization treatment, high temperature aging treatment, and low temperature aging treatment, the alloy has high endurance strength and
creep limit. The service life is greater than or equal to 200 h at the endurance condition of 1100 DEG C / 140 MPa, and the endurance strength ofthe alloy is comparable to that of CMSX-10; and the performance of high temperature
oxidation resistance is good, specifically, surface stability is good. A heat treatment window is wide, and
solid solution treatment is easy to control.