ASSEMBLY FOR AN AIRCRAFT TURBINE ENGINE, COMPRISING MEANS FOR THE AXIAL AND RADIAL RETENTION OF A FAN

An assembly for an aircraft turbine engine, includes a fan, a speed reduction gear and an intermediate casing including an internal annular structure that houses an epicyclic gear train equipped with a planet carrier. The assembly includes a secondary retention device for the ring gear of the planet...

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Bibliographische Detailangaben
Hauptverfasser: DESOMBRE, Didier, Gabriel, Bertrand, PAPIN, Thierry, Georges, Paul
Format: Patent
Sprache:eng ; fre ; ger
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Beschreibung
Zusammenfassung:An assembly for an aircraft turbine engine, includes a fan, a speed reduction gear and an intermediate casing including an internal annular structure that houses an epicyclic gear train equipped with a planet carrier. The assembly includes a secondary retention device for the ring gear of the planet carrier, the device including: first projections that project radially inwards from the internal annular structure, each first projection having a recess that is open radially inwards, axially downwards and circumferentially in a first direction; and second projections that project radially outwards from the ring gear of the planet carrier and cooperate with the first projections in such a way that each second projection is partially accommodated in the recess of the first projection with which it is associated and downstream therefrom.