Cantilevered stator stage
AssigneeROLLS-ROYCE plc
InventorLeo V Lewis
Life of this patent
Estimating the term…
Abstract
A cantilevered stator stage for the axial compressor 14 of a gas turbine engine 10 in which the stator tips 26 rub against an abrasive section 24 on the rotor drum 22 during initial running of the engine 10 to abrade the tips 26 of the stator to provide optimised stator tip running clearance.
Claims10
A cantilevered stator stage for a gas turbine engine, the stage comprising a plurality of stators circumferentially arranged around a rotor drum, with an abrasive section provided on the rotor drum facing the stators, the stage being arranged such that during initial running of the engine at least most of the stators rub against the abrasive section, to abrade the tips of the stators in which the tips of the stators are formed so as to facilitate abrasion thereof in which the stators have a reduced thickness towards the tips thereof.
A method of building a cantilevered stator stage for a gas turbine engine, the method comprising providing a plurality of stators circumferentially arranged around a rotor drum, providing an abrasive section on the rotor drum facing the stators, arranging the stator lengths such that during initial running of the engine at least most of the stators rub against the abrasive section, to abrade the tips of the stators.
Dependencies are inferred from the claim text.