COMPLIANT INTERMEDIATE COMPONENT OF A GAS TURBINE ENGINE

The present application provides an intermediate structure (130) in a gas turbine engine. The intermediate structure is positioned between a first component (120) and another component (110). The first component (120) may be a composite component. The components may be interlocking. The intermediate...

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Bibliographische Detailangaben
Hauptverfasser:	CHAMBERLAIN, ADAM L, USKERT, RICHARD C, THOMAS, DAVID J
Format:	Patent
Sprache:	eng ; fre
Schlagworte:	ARRANGEMENTS OR ADAPTATIONS OF HEATING, COOLING, VENTILATING,OR OTHER AIR-TREATING DEVICES SPECIALLY FOR PASSENGER OR GOODSSPACES OF VEHICLES BLASTING ENGINE PLANTS IN GENERAL HEATING LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES PERFORMING OPERATIONS STEAM ENGINES TRANSPORTING VEHICLES IN GENERAL WEAPONS
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Beschreibung
Zusammenfassung:	The present application provides an intermediate structure (130) in a gas turbine engine. The intermediate structure is positioned between a first component (120) and another component (110). The first component (120) may be a composite component. The components may be interlocking. The intermediate structure may be load bearing. Also disclosed is a method using the intermediate structure (130).