Aircraft turbomachine
AssigneeSafran Aircraft Engines
InventorsPaul Ghislain Albert Levisse, Julien Fabien Patrick Becoulet
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Abstract
Aircraft turbomachine comprising a casing, a fan, a compressor and a turbine and an epicyclic gear train comprising an input driven in rotation by the turbine, a first output stage configured to drive in rotation the compressor and a second output stage coupled to the first output stage and configured to drive in rotation the fan, the compressor being driven in rotation by the ring gear of the first output stage.
Claims13
An aircraft turbomachine comprising a casing, a fan, a compressor and a turbine, the casing comprising an inlet casing between the fan and the compressor, the turbomachine further comprising an epicyclic gear train comprising an input driven in rotation by the turbine, a first output stage configured to drive in rotation the compressor and a second output stage coupled to the first output stage and configured to drive in rotation the fan, the compressor being driven in rotation by a first ring gear, the first ring gear being the ring gear of the first output stage, wherein the first ring gear is radially outside of at least one planet gear of the first output stage.
Dependencies are inferred from the claim text.