Abstract: An assembly for aircraft turbomachine, including a stator part, a first bearing, a second bearing and a support part in an oil enclosure delimited by an outer enclosure delimiting portion integral with the stator part, the support part including a first axial end portion forming an outer ring of the first bearing, or supporting such a ring; a second axial end portion forming an outer ring of the second bearing or supporting such a ring, a compression damping oil film being arranged between the second portion and the stator part; an intermediate ring, arranged axially between the first and second portions, and forming a flexible connection as well as an oil-spray protection element.

Abstract: An assembly for aircraft turbomachine, including a stator part, a first bearing, a second bearing and a support part in an oil enclosure delimited by an outer enclosure delimiting portion integral with the stator part, the support part including a first axial end portion forming an outer ring of the first bearing, or supporting such a ring; a second axial end portion forming an outer ring of the second bearing or supporting such a ring, a compression damping oil film being arranged between the second portion and the stator part; an intermediate ring, arranged axially between the first and second portions, and forming a flexible connection as well as an oil-spray protection element.

Abstract: An aircraft turbomachine has a gas generator that includes, along a longitudinal axis (X), at least one compressor, a combustion chamber, and at least one turbine. The turbomachine further includes at least one duct for supplying liquid to at least one member chosen from an oil jet and a fuel injector. The duct (20) has rectilinear portions and bent portions and includes at least one region in which the liquid is liable to coke. The turbomachine also includes at least one turbulence element in the at least one region in the duct.