Frangible fan blade

Fluid reaction surfaces (i.e. – impellers) – Rotor having flow confining or deflecting web – shroud or... – Axially extending shroud ring or casing

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Details

F04D 2938

Patent

active

061460990

ABSTRACT:
A fan in an axial flow gas turbine engine includes a plurality of fan blades. Each fan blade includes an airfoil portion and a root portion with a platform disposed radially therebetween. The platform of each blade extends circumferentially from the blade and is dimensioned to define, with an adjacent platform, an enlarged gap to insure that contact between adjacent platforms is avoided when a blade is released during a blade loss condition. A seal is provided to seal the enlarged gap between adjacent platforms during normal operation of the gas turbine engine.

REFERENCES:
patent: 4714410 (1987-12-01), Hancock
patent: 4872810 (1989-10-01), Brown et al.
patent: 4917574 (1990-04-01), Dodd et al.
patent: 5281097 (1994-01-01), Wilson et al.
patent: 5302085 (1994-04-01), Dietz et al.
patent: 5573375 (1996-11-01), Barcza
patent: 5599170 (1997-02-01), Marchi et al.

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