Backswept turbojet blade

Details Backswept turbojet blade Backswept turbojet blade

2006-09-19

2006-09-19

Look, Edward K. (Department: 3745)

Fluid reaction surfaces (i.e., impellers)

Specific blade structure

Concave surface

C416S22300B

Reexamination Certificate

active

07108486

ABSTRACT:
A rotary turbojet blade comprises a plurality of blade sections extending along a line of the centers of gravity of said sections between a base and a tip, said blade presenting along a radial axis a bottom portion, an intermediate portion, and a top portion, said bottom portion presenting a longitudinal angle of inclination for a leading edge line, said intermediate portion presenting a backward longitudinal angle of inclination for said leading edge line, and said top portion presenting a backward longitudinal angle of inclination for said leading edge line and a tangential angle of inclination for said line of the centers of gravity in a direction opposite to the direction of rotation of said blade.

REFERENCES:
patent: 3989406 (1976-11-01), Bliss
patent: 6071077 (2000-06-01), Rowlands
patent: 6358003 (2002-03-01), Schlechtriem
patent: 6524070 (2003-02-01), Carter
patent: 0 774 567 (1997-05-01), None
patent: 0 801 230 (1997-10-01), None
patent: 1 106 836 (2001-06-01), None
patent: 1 126 133 (2001-08-01), None

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