Fan blade attachment for gas turbine engine

Details Fan blade attachment for gas turbine engine Fan blade attachment for gas turbine engine

1995-03-01

1996-03-26

Look, Edward K.

Fluid reaction surfaces (i.e., impellers)

With weight-balancing means

416220R, F01D 532

Patent

active

055015751

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.

REFERENCES:
patent: 4453890 (1984-06-01), Brantley
patent: 4730983 (1988-03-01), Naudet et al.
patent: 5067877 (1991-11-01), Youssef
patent: 5112193 (1992-05-01), Greer et al.
patent: 5156525 (1992-10-01), Ciokajlo

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