Patent ID: 7527476
Filing Date: 2009-05-05
Classification: F01D

Abstract:
1. A rotor assembly for a gas turbine engine compressor, the rotor assembly having a rotational axis and including: a rotor disc for mounting a plurality of radially extending rotor blades such that rotation of the rotor blades draws air through the rotor assembly; and an annulus filler being disposed on a circular surface of rotor disc to provide a radially inner airflow surface for air being drawn through the rotor assembly, wherein the rotor assembly includes a securing arrangement for securing the annulus filler to the circular surface of the rotor disc, and the annulus filler includes a resilient portion such that the annulus filler is radially outwardly biased relative to the rotational axis into a condition in which the securing arrangement mechanically retains the annulus filler on the circular surface of the rotor disc, but is movable against the bias to allow the annulus filler to be removed from the rotor disc, the annulus filler includes an axially forward end and an axially rear end, the airflow surface of the annulus filler extending substantially between the forward and the rear end, and the securing arrangement includes a forward retaining means provided at the forward end of the annulus filler, and a rear retaining means provided at the rear end of the annulus filler.