Rotor blade for a gas turbine engine

Details Rotor blade for a gas turbine engine Rotor blade for a gas turbine engine

1977-03-16

1978-10-17

Powell, Jr., Everette A.

Fluid reaction surfaces (i.e., impellers)

Having frangible or fusible part or connection

416193A, 416212A, 416248, F01D 530

Patent

active

041206070

ABSTRACT:
A rotor blade for a gas turbine engine comprises an aerofoil, an inner platform and a root portion. In order to restrain the movement of the blade should it become detached from its rotor, the platform has an indentation in that edge adjacent the convex flank. If the blade detaches, this indentation engages with the leading edge of the next adjacent blade in the row, tending to restrict motion of the detached blade to the radial plane.

REFERENCES:
patent: 2867408 (1959-01-01), Kolb et al.
patent: 3198485 (1965-08-01), Melenchuk
patent: 3575522 (1971-04-01), Melenchuk
patent: 3871791 (1975-03-01), Guy et al.
patent: 3986793 (1976-10-01), Warner et al.

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