FIELD: aviation.
SUBSTANCE: shaft system (22, 32) for aviation turbomachine (1) contains first outer shaft (32) and second inner shaft (22), wherein the first outer shaft is designed to be inserted along the axis into the second shaft, and it contains inner grooves (34) for mating with longitudinal outer grooves (24) of the second shaft. The system differs in that, when the first and the second shafts are in a mating position, inner and outer grooves engage with each other and interact with each other in axial mating zone (Z), while inner and outer gears are outside this mating zone.
EFFECT: invention provides optimal positioning of shaft grooves during their insertion.
12 cl, 12 dwg
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