A method for manufacturing a compressor rotor of an aircraft gas turbine engine having an axis of rotation and comprising the parts as follows, axially installed in a stack: - a sealing disk, for the seal between said compressor rotor and a combustion chamber, the sealing disk having mounting flanges, - at least one first rotor disk (27, 270), to be assembled with the sealing disk using the mounting flanges, - an intermediate disk comprising a stage of intermediate blades, - at least one second rotor disk (31, 310) defining rotor blade stages with said at least one first rotor disk (27, 270) and the intermediate disk, - an upstream portion of a shaft for a connection between said compressor rotor and a turbine, and - a primary disk defining a first one of the rotor blade stages, wherein, when installing said parts, said parts are stacked one on top of another and then assembled together, said method being characterised in that: - when installing the sealing disk on said at least one first rotor disk (27, 270) and/or the intermediate disk on said at least one first rotor disk assembled with the sealing disk, an axial packing is applied with a pressure ranging from 40 x 10 5 to 60 x 10 5 Pa, - prior to assembling the sealing disk with said at least one first rotor disk (27, 270), the sealing disk is heated to a temperature ranging from 80 °C to 140 °C, - when installing the intermediate disk on said at least one first rotor disk (27, 270) assembled with the sealing disk, the intermediate disk is heated to a temperature ranging from 120 °C to 160 °C, and then an axial packing is applied with a pressure ranging from 40 x 10 5 to 60 x 10 5 Pa, - when installing said at least one second rotor disk (31, 310) on the intermediate disk assembled with the at least one first rotor disk (27, 270), itself assembled with the sealing disk: -- a) an axial packing is applied with a pressure ranging from 40 x 10 5 to 60 x 10 5 Pa, -- b) said at least one second rotor disk (31, 310) is cooled down: --- b1) either to a temperature ranging from -70 °C to -110 °C, --- b2) or as a function of maximum outer diameters of the intermediate disk and of said at least one second rotor disk (31, 310), -- c) the intermediate disk is not heated again unless, during step b), the cooling temperature of said at least one second rotor disk (31, 310) was less than -130 °C, to within 10 °C. - a sealing disk, for the seal between said compressor rotor and a combustion chamber, the sealing disk having mounting flanges, - at least one first rotor disk (27, 270), to be assembled with the sealing disk using the mounting flanges, - an intermediate disk comprising a stage of intermediate blades, - at least one second rotor disk (31, 310) defining rotor blade stages with said at least one first rotor disk (27, 270) and the intermediate disk, - an upstream portion of a shaft for a connection between said compressor rotor and a turbine, and - a primary disk defining a first one of the rotor blade stages, - when installing the sealing disk on said at least one first rotor disk (27, 270) and/or the intermediate disk on said at least one first rotor disk assembled with the sealing disk, an axial packing is applied with a pressure ranging from 40 x 10 5 to 60 x 10 5 Pa, - prior to assembling the sealing disk with said at least one first rotor disk (27, 270), the sealing disk is heated to a temperature ranging from 80 °C to 140 °C, - when installing the intermediate disk on said at least one first rotor disk (27, 270) assembled with the sealing disk, the intermediate disk is heated to a temperature ranging from 120 °C to 160 °C, and then an axial packing is applied with a pressure ranging from 40 x 10 5 to 60 x 10 5 Pa, - when installing said at least one second rotor disk (31, 310) on the intermediate disk assembled with the at least one first rotor disk (27, 270), itself assembled with the sealing disk: -- a) an axial packing is applied with a pressure ranging from 40 x 10 5 to 60 x 10 5 Pa, -- b) said at least one second rotor disk (31, 310) is cooled down: --- b1) either to a temperature ranging from -70 °C to -110 °C, --- b2) or as a function of maximum outer diameters of the intermediate disk and of said at least one second rotor disk (31, 310), -- c) the intermediate disk is not heated again unless, during step b), the cooling temperature of said at least one second rotor disk (31, 310) was less than -130 °C, to within 10 °C. -- a) an axial packing is applied with a pressure ranging from 40 x 10 5 to 60 x 10 5 Pa, -- b) said at least one second rotor disk (31, 310) is cooled down: --- b1) either to a temperature ranging from -70 °C to -110 °C, --- b2) or as a function of maximum outer diameters of the intermediate disk and of said at least one second rotor disk (31, 310), --- b1) either to a temperature ranging from -70 °C to -110 °C, --- b2) or as a function of maximum outer diameters of the intermediate disk and of said at least one second rotor disk (31, 310), -- c) the intermediate disk is not heated again unless, during step b), the cooling temperature of said at least one second rotor disk (31, 310) was less than -130 °C, to within 10 °C.