An axial turbomachine (2; 102; 202), such as an aircraft turbojet, the turbomachine (2; 102; 202) comprising a fan (18; 118), and a flow path, crossing: - an upstream compressor (24; 124) with an upstream rotor (26; 126) and stator vanes (58; 158), - a downstream compressor (32; 132) with a downstream rotor (34; 134) and stator vanes (58; 158), and - a central compressor (28; 128) with a central rotor (30; 130) positioned between the upstream rotor (26; 126) and the downstream rotor (34; 134), and fitted with stator vanes (58; 158); the axial turbomachine (2; 102; 202) further comprising a reducer (44; 144; 244) coupled to the upstream rotor (26; 126) and to the central rotor (30; 130) so as to reduce the rotation speed of the upstream rotor (26; 126) in relation to the rotation speed of the central rotor (30; 130), the upstream rotor (26; 126) being secured to the fan (18; 118), and the turbomachine comprising an annular splitter nozzle axially positioned between the fan (18; 118) and the upstream compressor (24; 124), characterized in that the upstream compressor (24; 124) comprises an axial play between the blades (60; 160) of the upstream rotor (26; 126) and the stator vanes (58; 158) of the upstream compressor (26; 126), such axial play being larger than the axial play of the central compressor (28; 128) between the blades (60; 160) of the central rotor (30; 130) and the stator vanes (58; 158) of the central compressor (28; 128). - an upstream compressor (24; 124) with an upstream rotor (26; 126) and stator vanes (58; 158), - a downstream compressor (32; 132) with a downstream rotor (34; 134) and stator vanes (58; 158), and - a central compressor (28; 128) with a central rotor (30; 130) positioned between the upstream rotor (26; 126) and the downstream rotor (34; 134), and fitted with stator vanes (58; 158); the axial turbomachine (2; 102; 202) further comprising a reducer (44; 144; 244) coupled to the upstream rotor (26; 126) and to the central rotor (30; 130) so as to reduce the rotation speed of the upstream rotor (26; 126) in relation to the rotation speed of the central rotor (30; 130), the upstream rotor (26; 126) being secured to the fan (18; 118), and the turbomachine comprising an annular splitter nozzle axially positioned between the fan (18; 118) and the upstream compressor (24; 124), characterized in that the upstream compressor (24; 124) comprises an axial play between the blades (60; 160) of the upstream rotor (26; 126) and the stator vanes (58; 158) of the upstream compressor (26; 126), such axial play being larger than the axial play of the central compressor (28; 128) between the blades (60; 160) of the central rotor (30; 130) and the stator vanes (58; 158) of the central compressor (28; 128). the axial turbomachine (2; 102; 202) further comprising a reducer (44; 144; 244) coupled to the upstream rotor (26; 126) and to the central rotor (30; 130) so as to reduce the rotation speed of the upstream rotor (26; 126) in relation to the rotation speed of the central rotor (30; 130), the upstream rotor (26; 126) being secured to the fan (18; 118), and the turbomachine comprising an annular splitter nozzle axially positioned between the fan (18; 118) and the upstream compressor (24; 124), characterized in that the upstream compressor (24; 124) comprises an axial play between the blades (60; 160) of the upstream rotor (26; 126) and the stator vanes (58; 158) of the upstream compressor (26; 126), such axial play being larger than the axial play of the central compressor (28; 128) between the blades (60; 160) of the central rotor (30; 130) and the stator vanes (58; 158) of the central compressor (28; 128).