IMPROVED METHOD FOR MANUFACTURING A MECHANICAL REDUCTION GEAR FOR AN AIRCRAFT TURBINE ENGINE

A method for manufacturing a mechanical reducer for an aircraft turbomachine including a central pinion, an outer crown, N planet pinions, where N≥3, each planet pinion including a first stage meshing with the central pinion, and a second stage meshing with the outer crown, the method including the...

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Bibliographische Detailangaben
Hauptverfasser:	GHRIBI, Dhafer, SIMON, Adrien Louis
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ENGINEERING ELEMENTS AND UNITS GAS-TURBINE PLANTS GEARING GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVEFUNCTIONING OF MACHINES OR INSTALLATIONS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION PLANTS LIGHTING MECHANICAL ENGINEERING THERMAL INSULATION IN GENERAL WEAPONS
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Beschreibung
Zusammenfassung:	A method for manufacturing a mechanical reducer for an aircraft turbomachine including a central pinion, an outer crown, N planet pinions, where N≥3, each planet pinion including a first stage meshing with the central pinion, and a second stage meshing with the outer crown, the method including the assembly marking, wherein N teeth of the central pinion are marked, and N pairs of teeth of the first stage of each planet pinion are marked, the N planet pinions each being marked identically, and the assembly of the mechanical reducer, so that the teeth of the pairs of marked teeth of the first stage of each planet pinion are disposed on either side of a marked tooth of the central pinion.