BLADE CONTAINMENT SYSTEM FOR GAS TURBINE ENGINE

PROBLEM TO BE SOLVED: To provide a blade containment system for a gas turbine engine. SOLUTION: The blade containment system 62 includes an annular casing 40 provided at radially outside of the blade 44 in a relation for surrounding a blade 44. The annular casing 40 includes at least one layer of fi...

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Bibliographische Detailangaben
Hauptverfasser:	CRALL DAVID WILLIAM, XIE MING, LACHAPELLE DONALD GEORGE, WORTHOFF FRANK, BEDEL DAVID LAWRENCE, MITCHELL STEPHEN C, LANGENBRUNNER LESILE LOUIS
Format:	Patent
Sprache:	eng
Schlagworte:	BLASTING COMBUSTION ENGINES ENGINE PLANTS IN GENERAL HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION PLANTS LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES WEAPONS
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Beschreibung
Zusammenfassung:	PROBLEM TO BE SOLVED: To provide a blade containment system for a gas turbine engine. SOLUTION: The blade containment system 62 includes an annular casing 40 provided at radially outside of the blade 44 in a relation for surrounding a blade 44. The annular casing 40 includes at least one layer of fiber metal laminate layer 78 which is used with the casing. The blade containment system 62 may include a honeycomb layer 64 provided at a radially outside of an inside part 66 of the annular casing 40 and the fiber metal laminate layer 78 is positioned at radially outside or at radially inside of the honeycomb layer 64. In both the cases, the blade containment system 62 may also include a Kevlar wrap layer 82 which is at radially outside. COPYRIGHT: (C)2008,JPO&INPIT