公开(公告)号：US20190338707A1

公开(公告)日：2019-11-07

申请号：US16386542

申请日：2019-04-17

Applicant: Rolls-Royce plc

Inventor： Peter A. Beecroft ,  Gareth M. Armstrong ,  Bharat R. Koli ,  Alastair D. Walker

IPC: F02C7/18

Abstract: The present disclosure relates to a compressor assembly for a gas turbine engine. The compressor assembly comprises a compressor having a compressor stage with a plurality of rotor blades mounted on the rim of a rotor disc within a core air flow path. There is a purge channel extending from a radially inner purge gas source to at least one radially outer outlet at the rim of the compressor stage. The purge channel comprises at least one swirl element and/or at least one orifice for swirling/deflecting a purge gas flowing within the purge channel. In use, a flow of purge gas exits the outlet(s) at least partly in the direction of the core air flow path.