CPC F02C 3/067 (2013.01) [F02C 7/06 (2013.01); F02C 7/36 (2013.01); F05D 2260/40311 (2013.01); F05D 2260/98 (2013.01)] | 13 Claims |
1. A turbomachine with a counter-rotating turbine for an aircraft,
the turbomachine comprising a counter-rotating turbine a first rotor of which is configured to rotate in a first direction of rotation and is connected to a first turbine shaft, and a second rotor is configured to rotate in an opposite direction of rotation and is connected to a second turbine shaft, the first rotor comprising turbine wheels interposed between turbine wheels of the second rotor,
the turbomachine further comprising a mechanical reduction gear with an epicyclic gear train of the planetary type which comprises a sun gear driven in rotation by said second shaft, a ring gear driven in rotation by said first shaft, and a planet carrier attached to a stator casing of the turbomachine located upstream of the counter-rotating turbine with respect to a direction of flow of the gases in the turbomachine,
wherein the planet carrier is attached to the stator casing by means of an annular part with an elongated shape extending inside said second shaft, the part comprising an upstream end attached to the intermediate casing and a downstream end coupled to the planet carrier, and the part comprises an integrated circuit for conveying lubricating oil from its upstream end to the planet carrier.
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