Support for a degassing tube for an aircraft turbomachine

Abstract

Support (30) for a degassing tube for an aircraft turbomachine, the support (30) comprising an annular inner wall (41) which internally defines a degassing channel (42) through which an exhaust air stream (Fae) from a lubrication chamber flows, the support (30) comprising an annular outer wall (43) which extends directly around the inner wall (41), the outer wall (43) being coaxial with the inner wall (41) and at a distance from the inner wall (41), the inner and outer walls (41, 43) radially defining between them an annular passage (44) for cooling and thermal insulation, the outer wall (43) comprising an inlet (45) configured to introduce a compressed air stream (Fac) into the passage (44), the inner wall (41) comprising an outlet (46) which is connected to an ejection nozzle (34), the nozzle ejection (34) being configured to eject the airflow (Fac) from the passage (44) to the degassing path (42).Figure for the abridged version: 3.

Images