Perforated Drum of a Compressor of an Axial Turbine Engine

摘要

A rotor, in particular a drum of a low-pressure compressor of a turbojet aero engine, is disclosed. The rotor includes an outer annular wall delimiting a primary annular flow of the turbine engine, sealing devices with two rubbing strips or annular ribs formed on the wall. The rubbing strips cooperate by abrasion with inner shrouds. In addition, the annular wall includes rows of intake orifices for leakages which are arranged between each pair of rubbing strips in order to aspirate the recirculation leakages there. A plenum for leakages is formed inside the rotor by means of a composite partitioning, then evacuates the parasitic flow downstream of the turbine engine via the central shaft.

主权项

1. A rotor of an axial turbine engine, the rotor comprising:
a rotation axis; an outer annular wall around the rotation axis; and a sealing device formed on the wall, wherein the annular wall comprises:
at least one intake orifice for leakages, the intake orifice being disposed within the sealing device in order to divert the leakages therefrom and to evacuate the leakages axially beyond the rotor.