Aircraft turbomachine comprising a bearing support having an improved design

An assembly for an aircraft turbomachine, comprising:

• a stator part,
• a second bearing, and
• a support part, the second bearing and the support part being arranged in an oil enclosure delimited radially outwards by an outer enclosure delimiting portion integral with the stator part, the support part comprising:
• a first axial end portion;
• a fastening portion of the support part on the stator part, the fastening portion being connected to the first axial end portion;
• a second axial end portion opposite the first axial end portion, and forming or supporting an outer ring of the second bearing, a compression damping oil film being arranged between an outer surface of the second axial end portion and a corresponding surface of the stator part;
• and
• an intermediate ring, arranged axially between the first and second axial end portions, and forming a flexible connection between the same two axial end portions,
• wherein the intermediate ring further forms an oil spray protection element configured to prevent oil spraying from the interior of this intermediate ring against the outer enclosure delimiting portion,
• wherein the oil spray protection element includes orifices, a smallest dimension of each orifice being less than 5 mm, and solid portions delimiting said orifices, and
• wherein a ratio between a cumulative surface area of the orifices, and a total surface area of the protection element, is between 0.2 and 0.5.