Blade containment system for a gas turbine engine

Details Blade containment system for a gas turbine engine Blade containment system for a gas turbine engine

F - Mech Eng,Light,Heat,Weapons

01

D

F01D 21/00 (2006.01) B32B 3/12 (2006.01) B32B 15/02 (2006.01) B32B 15/08 (2006.01) F01D 25/24 (2006.01)

Patent

CA 2602319

In a gas turbine engine (10) having a plurality of radially extending blades (44) mounted on an annular disk (40), the blades (44) and disk (40) being rotatable about a longitudinal axis (12) of the engine (10), a blade containment system (62) including an annular casing (40) positioned radially outward of the blades (44) and in surrounding relationship therewith, with the annular casing (40) including at least one layer of fiber metal laminate (78) utilized therewith. The blade containment system (62) may also include a honeycomb layer (64) positioned radially exterior of an inner portion (66) of the annular casing (40), wherein the layer of fiber metal laminate (78) is positioned radially exterior of the honeycomb layer (64) or radially interior thereof. For both cases, the blade containment system (62) could include a radially exterior layer of Kevlar wrap (82).

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