High-temperature alloy for aircraft engine and manufacturing method and application of high-temperature alloy

The invention discloses a high-temperature alloy for an aircraft engine and a manufacturing method and application of the high-temperature alloy for the aircraft engine. 0.80% or less of silicon; less than or equal to 2.20% of manganese; less than or equal to 0.030% of sulfur; less than or equal to 0.030% of phosphorus; 18 to 24.0% of chromium; 4.5 to 6.5% of tungsten; 2.00% to 3.80% of molybdenum; 0.001% to 0.012% of boron; 0.70% to 1.60% of niobium; 0.010% to 0.30% of nitrogen; 0.05% to 0.40% of vanadium; 0.01% to 0.10% of aluminum; 0.50% or less of copper, and the balance Fe and inevitable impurities. According to the high-temperature alloy for the aircraft engine, oxide and sulfide are both smaller than or equal to 1.0 grade; the mechanical properties at the high temperature of 750 DEG C are as follows: the tensile strength is greater than or equal to 400N/mm < 2 >, and the elongation The oxygen content is less than or equal to 20ppm; the hydrogen content is less than or equal to 3ppm ...