Fan blade attachment for gas turbine engine
AssigneeUnited Technologies Corporation
InventorsDavid A. Eldredge, Robert A. Ress, Jr.
Life of this patent
Estimating the term…
Abstract
The attachment of the blade to the disk of a gas turbine engine includes a sloped deep slot formed in the rim of the disk for accepting the dovetail of the root of he fan or compressor blade allowing the removal of a single blade from the disk and includes a segmented retainer plate disposed at the aft end of the bearing against the blade root to react out the slope induced axial blade loads providing a low hub-tip ratio configuration. A blade support disposed between the live rim of the disk and the bottom of the blade serves to support the blades radially during non-operating conditions and includes pockets for retaining weights for dynamic balance of the rotor. A forward mounted snap ring prevents forward movement of the blade during non-operating conditions.
Claims19
Attachment means for a rotor having a disk and a plurality of circumferentially spaced blades, said disk having, a fore end, and aft end, and a rim area including a plurality of cicumferentially spaced axially sloped slots formed in said rim area, a flange radially extending from said rim area adjacent one end of each of said plurality of sloped slots, an annular retainer plate having a fore face and aft face, a portion at the inner diameter of said annular retainer plate fitted into an annular groove formed in said disk, a portion of said fore face extending radially beyond said annular groove bearing against said flange, an axially disposed support structure bearing against a portion of said aft face, and means for attaching said annular retainer plate to said flange and said support structure whereby the axial loads produced by said blades during rotation of said disk are reacted by said annular retainer plate so that said blade can be configured to have a low hub to tip ratio for high speed rotation.
Attachment means for a fan or compressor rotor for a gas turbine engine, said rotor having a disk including a fore end and an aft end, a plurality of circumferentially spaced blades, and a rim area including a plurality of cicumferentially spaced axially sloped slots formed in said rim area, a flange radially extending from said disk in said rim area adjacent one end of each of said plurality of sloped slots, an annular retainer plate having a fore face and aft face, a portion at the inner diameter of said annular retainer plate fitted into an annular groove formed in said disk, a portion of said fore face extending radially beyond said annular groove bearing against said flange, an axially disposed support structure bearing against a portion of said aft face, and tie bolt means for attaching said annular retainer plate to said flange and said support structure whereby the axial loads produced by said blades during rotation of said disk are reacted by said annular retainer plate so that said blade can be configured to have a low hub to tip ratio for said fan or compressor to operate at relatively high rotational speeds.
Dependencies are inferred from the claim text.