Balancing ring anti-rotation spacer
AssigneePratt & Whitney Canada Corp.
InventorHugues PELLERIN
Life of this patent
Estimating the term…
Abstract
A rotating assembly for a gas turbine engine has a balancing ring mounted to a first rotating component having a rotating unbalance about an axis of rotation. The ring is clocked at a circumferential position about the axis to counteract the rotating unbalance. A spacer is axially abutted against the first rotating component to set an axial position of the first rotating component relative to a second rotating component. The balancing ring is locked against rotation relative to the first rotating component in its circumferential position by the dual use spacer.
Claims20
A rotating assembly for a gas turbine engine, comprising:
- a first rotating component mounted for rotation about an axis;
- at least one balancing ring mounted to the first rotating component and clocked at a circumferential position about the axis to counteract a rotating unbalance of the first rotating component;
- and
- a spacer axially abutted against the first rotating component to set an axial position of the first rotating component relative to a second rotating component of the rotating assembly, the spacer locking the at least one balancing ring against rotation relative to the first rotating component.
A rotating assembly of a gas turbine engine, comprising:
- a first rotating component mounted to a shaft for rotation therewith about an axis;
- at least one circlip mounted to the first rotating component, the at least one circlip having a center of mass offset from the axis, the at least one circlip being adjustably rotatable relative to the first component about the axis to a circumferential position in which the at least one circlip counters a rotating unbalance of the first rotating component;
- and
- a spacer axially clamped between the first rotating component and a second rotating component of the rotating assembly, the spacer having scallops circumferentially spaced apart along a circumferential surface thereof around the axis, the scallops engageable with lugs projecting from the at least one circlip for locking the at least one circlip against rotation relative to the first component.
A method of balancing a first rotating component of a stack of rotating components of a gas turbine engine, the first rotating component mounted for rotation about an axis of rotation, the method comprising:
- mounting at least one circlip in a corresponding seat on the first rotating component, the at least one circlip having a center of mass offset from the axis of rotation;
- adjusting an angular orientation of the at least one circlip relative to the first rotating component, including rotating the at least one circlip about the axis of rotation to a circumferential position in which the at least one circlip counters a rotating unbalance of the first rotating component;
- and
- locking the at least one circlip against rotation relative to the first rotating component using a spacer axially clamped between the first rotating component and a second rotating component of the stack of rotating component.
Dependencies are inferred from the claim text.