Gas turbine engine fan blade retention

Details Gas turbine engine fan blade retention Gas turbine engine fan blade retention

1997-07-01

1999-06-22

Ryznic, John E.

Fluid reaction surfaces (i.e., impellers)

Specific working member mount

Blade received in well or slot

416219R, B63H 120

Patent

active

059136600

ABSTRACT:
A fan for a gas turbine engine comprises a rotary disc carrying an annular array of radially extending fan blades. Each fan blade has a root portion which is radially constrained within a generally axially extending groove formed within a disc rim. The blade root comprises two portions each radially convergent toward one another with respect to the axis of rotation of the disc. The groove within the disc also comprises two base portions each being correspondingly radially convergent toward one another. Axial retention of the blade root within the groove is achieved by the centrifugal component of the blade load acting in an opposite direction to any applied axial load in the forward or rearward direction.

REFERENCES:
patent: 2445154 (1948-07-01), Reed
patent: 2974924 (1961-03-01), Rankin et al.
patent: 3165294 (1965-01-01), Anderson
patent: 3986793 (1976-10-01), Warner et al.
patent: 4343593 (1982-08-01), Harris
patent: 4527952 (1985-07-01), Forestier et al.
patent: 4995788 (1991-02-01), Turnberg

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