Staggered fan blade assembly for a turbofan engine

Details Staggered fan blade assembly for a turbofan engine Staggered fan blade assembly for a turbofan engine

1991-09-11

1994-04-05

Look, Edward K.

Fluid reaction surfaces (i.e., impellers)

Unsymmetrical impeller or dissimilar working members

416223A, F01D 514

Patent

active

052999149

ABSTRACT:
A turbofan gas turbine engine fan stage having alternating relatively rugged, preferably hollow titanium, blades and staggered relatively less rugged, preferably composite, blades. The blades are staggered such that the leading edges of the rugged titanium blades are positioned forward of the leading edges of the less rugged composite blades. One embodiment provides that all fan blades have trailing edges at the same axial position while another embodiment provides that all fan blades are of the same size and shape.

REFERENCES:
patent: 2222444 (1940-11-01), Schmidt et al.
patent: 2839239 (1958-06-01), Stalker
patent: 3347520 (1967-10-01), Owczarek
patent: 3536417 (1970-10-01), Stiefel et al.
patent: 3703211 (1972-11-01), Bernaerts
patent: 4720239 (1988-01-01), Owczarek

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