Manufacturing process of large rotor shaft forgings with high toughness and long life for aviation

Abstract

The invention discloses a manufacturing process of a large-size rotor shaft forging member having characteristics of high toughness and long service life and used for aerospace. The process steps comprise: raw material smelting, homogenization heating, material discharging, heating before forging, cogging, normalizing, coarse machining UT inspection, macrostructure detection and non-metallic inclusion detection, heating before forging, high temperature forging, cold deformation strengthening, cyclic heat treatment, sub-temperature quenching, cryogenic treatment, tempering, coarse machining flaw detection, and fine machining processing. According to the present invention, the technical indexes of the rotor shaft forging member produced by using the manufacturing process comprise that the tensile strength Rm (MPa) is more than or equal to 1250, the yield strength Rp0.2 (MPa) is more than or equal to 1100, the elongation A (%) is more than or equal to 10, the cross section shrinkage rateZ (%) is more than or equal to 45, the hardness HRC is more than or equal to 38, the impact energy (J) is more than or equal to 40, the fracture toughness K1C (MPa.m<1 / 2>) is more than or equal to 100, the grain size is not thicker than grade 5, and the rotary bending fatigue limit is not less than 600M Pa (Kt=1, R=-1).

Description

technical field [0001] The invention relates to the field of forging shaft forgings, in particular to a manufacturing process of high-toughness and long-life large rotor shaft forgings for aviation. Background technique [0002] Shaft forgings, as high-speed rotating parts, require high strength, high toughness and high fatigue resistance. There is an existing large-scale rotor shaft forging for aviation that needs to meet the following technical requirements: tensile strength Rm (MPa) ≥ 1250, yield strength Rp0.2 (MPa) ≥ 1100, elongation A (%) ≥ 10, reduction of area Z (%) ≥ 45, hardness HRC ≥ 38, impact energy (J) ≥ 40, fracture toughness K 1C (MPa·m 1 / 2 ) ≥ 100, the grain size is not coarser than grade 5, and the rotational bending fatigue limit is not less than 600MPa (Kt=1, R=-1); however, the shaft forgings produced by the existing shaft forging manufacturing process cannot reach the above technical requirements. Contents of the invention [0003] The technical p...

AI Technical Summary

Problems solved by technology

There is an existing large-scale rotor shaft forging for aviation that needs to meet the following technical requirements: tensile strength Rm (MPa) ≥ 1250, yield strength Rp0.2 (MPa) ≥ 1100, elongation A (%) ≥ 10, reduction of area Z (%) ≥ 45, hardness HRC ≥ 38, impact energy (J) ≥ 40, fracture toughness K 1C (MPa·m 1 / 2 ) ≥ 100, the grain size is not coarser than grade 5, and the rotational bending fatigue limit is not less than 600MPa (Kt=1, R=-1); however, the shaft forgings produced by the existing shaft forging manufacturing process cannot reach the above technical requirements