Blade fixing design for protecting against low speed rotation induced wear
AssigneePratt & Whitney Canada Corp.
InventorsBarry Barnett, Philippe Bonniere
Life of this patent
Estimating the term…
Abstract
The blade dovetails and associated dovetail slots of a gas turbine engine rotor assembly are shaped so that during windmilling the high stress regions of the blade dovetails are shielded from rubbing against the disk and vice versa. Bumper surfaces are provided in low stress regions of the dovetail assembly such that the windmilling contact points between the blade dovetails and the disk are in non-critical areas of the dovetail assembly.
Claims11
A fan rotor assembly of a gas turbine engine, comprising a disk mounted for rotation about a centerline of the engine, an array of circumferentially distributed dovetail slots defined in an outer periphery of the disk, a corresponding array of fan blades attachable to the disk, each fan blade having a blade dovetail engageable in a corresponding one of the dovetail slots, the blade dovetail having high stress regions and low stress regions, the low stress regions having a sacrificial bumper which will wear in preference to the high stress regions of the blade dovetail, the sacrificial bumper providing for a closer tolerance fit of the low stress regions of the blade dovetail in the dovetail slots than the high stress regions, thereby shielding the high stress regions from rubbing against the disk when the rotational speed of the turbofan assembly is too low to centrifugally lock the fan blades in position on the disk, wherein each dovetail slot has a pair of outer overhanging lugs having radially inwardly facing bearing surfaces for engagement with corresponding bearing surfaces provided on opposed flanks of each blade dovetail, wherein the sacrificial bumper comprises a pair of bumper surfaces provided on each blade dovetail radially outwardly of the bearing surfaces thereof for engaging corresponding bumper surfaces provided at a mouth of each dovetail slot, wherein the bumper surfaces of the blade dovetails and the bumper surfaces of the dovetail slots are oriented to be in contact while the blades move radially inwardly and outwardly relative to the dovetail slots during windmilling, and wherein the high stress regions of the blade dovetails include a neck region disposed radially between the bumper surfaces and the bearing surfaces of the blade dovetails, the bumper surfaces shielding the neck region along a full axial extent thereof from contacting the disk when the fan rotor assembly rotates at low speed, and wherein contact points between the blade dovetails and the disk during windmilling are in the low stress regions only.
A gas turbine engine fan rotor assembly comprising a rotor disk mounted for rotation about an axis and having a plurality of fan blade mounting slots circumferentially distributed about a periphery of the rotor disk for receiving complementary blade fixing portions of a set of fan blades, wherein each blade fixing portion has low stress regions and high stress regions, and wherein bumper surfaces are provided in the low stress regions away from the high stress regions so that during windmilling when the rotational speed of the rotor assembly is too low to centrifugally lock the fan blades in position on the disk, the bumper surfaces contact the disk and shield the high stress regions from contacting the disk, thereby protecting the high stress regions of the blade fixing portions from windmilling induced wear, wherein the blade fixing portions are shaped so that only the low stress regions rub against the disk during windmilling induced movement of the blades in the blade mounting slots, wherein the high stress regions include a blade neck peak stress region having a length extending axially from a front end to a rear end of the blade fixing portion of each fan blade, and wherein the bumper surfaces include a pair of opposed axially extending sidewall surfaces disposed radially outwardly of the blade neck peak stress region relative to the axis of the rotor disk for engagement with corresponding axially extending bumper surfaces provided at a mouth of a corresponding one of said blade mounting slots, wherein the axially extending sidewall surfaces disposed radially outwardly of the blade neck peak stress region relative to the axis of the rotor disk and the corresponding axially extending bumper surfaces provided at the mouth of the corresponding one of said blade mounting slots are oriented to be in contact while the blades move radially inwardly and outwardly relative to the blade mounting slots during windmilling, the both corresponding bumper surfaces shielding blade neck peak stress region along the full length thereof from rubbing against the disk during windmilling.
Dependencies are inferred from the claim text.