Blading system for a gas turbine engine

Details Blading system for a gas turbine engine Blading system for a gas turbine engine

1981-06-18

1984-06-12

Coe, Philip R.

Fluid reaction surfaces (i.e., impellers)

Specific working member mount

Blade received in well or slot

416221, B63H 120, B64C 1104

Patent

active

044538901

ABSTRACT:
In one embodiment, a fan blade includes an airfoil portion, a platform portion, a shank portion, and a generally axial dovetail portion of a predetermined axial dimension for matingly engaging a generally axial dovetail receiving slot of substantially the same predetermined axial dimension in a fan disk member. Aft cleat means, including a portion having substantially the same cross section as the dovetail portion, is provided and is integral with the dovetail portion and projects generally axially therefrom. The aft cleat means strengthens the dovetail portion. Methods are provided for fabricating such a blade and for strengthening existing blades. Other embodiments are disclosed.

REFERENCES:
patent: 3055633 (1962-09-01), Pouit
patent: 3458119 (1969-07-01), Shaw
patent: 3572970 (1971-03-01), Smuland
patent: 3734646 (1973-05-01), Perkins
patent: 4006999 (1977-02-01), Brantley et al.
patent: 4221542 (1980-09-01), Acres et al.
patent: 4265595 (1981-05-01), Bucy, Jr. et al.
General Electric Company Program Review to Air France, KLM, Lufthansa Air Lines on Jul. 9, 1980, p. D10325-051380.

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