公开(公告)号：US11015458B2

公开(公告)日：2021-05-25

申请号：US16797414

申请日：2020-02-21

Applicant: ROLLS-ROYCE plc

Inventor： Roderick M Townes ,  Neal Carter ,  Thomas W Martin

IPC: F01D11/08 ,  F01D5/22

Abstract: A turbomachine for a gas turbine engine, comprising: a rotor disc arranged to rotate about a fixed central axis. A plurality of rotor blades connected to the rotor disc, wherein the rotor blades extend within a gas flow path. A rotating annulus is arranged to rotate in a fixed rotational alignment relative to the rotor disc. An outer surface of the rotating annulus is arranged to define part of the boundary of the gas flow path. A gas turbine engine for an aircraft and a method of defining the boundary of a gas flow path within a turbomachine is also disclosed.