Lubricated enclosure for an aircraft turbine engine, limiting the retention of lubricant during pitching

A lubricated enclosure for an aircraft turbine engine, the enclosure comprising:

• a drained rolling bearing provided with drainage holes;
• a lubricant ejector configured to limit the retention of lubricant in a critical area of the enclosure, said ejector being configured to be traversed by a primary lubricant flow in order to drive a secondary lubricant flow located around a nozzle of the ejector housed in said critical area of the enclosure;
• and
• a communication device for communicating the drainage holes with the ejector, so that the lubricant escaping from the drainage holes supplies the ejector in order to form the primary flow,
• wherein the secondary flow is sucked into the nozzle under effect of the primary lubricant flow flowing through the nozzle.