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A turbine engine fan disk including a cylindrical rim including in its outer periphery substantially axial slots for mounting blade roots and opening out to a radially upstream face of the rim is provided. A shroud extends from the rim and connects with a rotary drive shaft. A cylindrical lip extend

A turbine engine fan disk including a cylindrical rim including in its outer periphery substantially axial slots for mounting blade roots and opening out to a radially upstream face of the rim is provided. A shroud extends from the rim and connects with a rotary drive shaft. A cylindrical lip extends upstream from the upstream face of the rim. The inside surface of the disk having a cylindrical portion extended upstream by a portion of greater diameter that forms a setback that is axially offset upstream relative to the upstream radial face of the rim.

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1. A turbine engine fan disk having an axis and comprising: a rim including slots, at a radially outer periphery, for mounting blade roots in the slots, the slots opening out to an upstream radial face of the rim;a shroud extending from the rim and connecting with a rotary drive shaft; anda lip exte

1. A turbine engine fan disk having an axis and comprising: a rim including slots, at a radially outer periphery, for mounting blade roots in the slots, the slots opening out to an upstream radial face of the rim;a shroud extending from the rim and connecting with a rotary drive shaft; anda lip extending upstream from the upstream radial face of the rim, the lip having a radially inside surface provided with a concave setback which is offset both:axially upstream relative to the upstream radial face of the rim, andradially relative to a radially inside surface of the disk. 2. The turbine engine fan disk according to claim 1, wherein the setback is offset axially from the upstream radial face of the rim by an axial distance lying in the range 1 mm to 3 mm. 3. The turbine engine fan disk according to claim 1, wherein the radially inside surface of the disk includes a frustoconical portion flaring downstream and extending to a downstream end of the rim. 4. A turbine engine fan disk according to claim 3, wherein the angle of the frustoconical portion lies in the range 1° to 10°. 5. The turbine engine fan disk according to claim 4, wherein the angle of the frustoconical portion is about 3°. 6. A turbine engine fan disk having an axis and comprising: a rim including slots, at a radially outer periphery, for mounting blade roots in the slots, the slots opening out to an upstream radial face of the rim;a shroud extending from the rim and connecting with a rotary drive shaft;a lip extending upstream from an upstream radial face of the rim, the lip having a radially inside surface provided with a concave setback which is offset both: axially upstream relative to the upstream radial face of the rim, andradially relative to a radially inside surface of the disk,wherein the lip has a radially outside surface that includes an annular groove in which a ring is partially engaged, for retaining blades. 7. The turbine engine fan disk according to claim 1, wherein the disk has a radially inner surface having a cylindrical portion at an upstream end, the cylindrical portion extending parallel to the axis and having a length lying in the range 10 mm to 20 mm. 8. The turbine engine fan disk according to claim 1, wherein it does not include balance weights or balance hub. 9. A turbine engine, including a turbine engine fan disk according to claim 1. 10. The turbine engine fan disk according to claim 1, wherein the lip has a radially outside surface that includes an annular groove in which a ring is partially engaged, for retaining blades. 11. The turbine engine fan disk according to claim 10, wherein the annular groove is defined by an upstream radial face of the disk and by a flange of the lip extending radially outwards. 12. The turbine engine fan disk according to claim 1, wherein the radially inside surface of the disk has a frustoconical portion that flares downstream. 13. The turbine engine fan disk according to claim 6, wherein the ring includes an upstream inner radial surface which abuts an outer radial surface of the flange of the lip, and a downstream outer radial surface which abuts an inner radial surface of a spacer interposed between one of the blade roots and one of the slots. 14. The turbine engine fan disk according to claim 6, wherein the groove is defined by an upstream radial face of the disk and by a flange of the lip extending radially outwards. 15. The turbine engine fan disk according to claim 6, wherein the radially inside surface of the disk has a frustoconical portion that flares downstream.