Gehäuse für eine Gasturbine

A gas turbine engine is provided with a translatable cowl and a cascade structure which is nested within the translatable portion of the cowl. The cascade structure comprises C shaped sections which are exposed upon translation of a portion of the cowl. The C shaped sections are capable of rotation...

Ausführliche Beschreibung

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Bibliographische Detailangaben
1. Verfasser:	NEWTON, ARNOLD CHARLES
Format:	Patent
Sprache:	ger
Schlagworte:	AIRCRAFT ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT AVIATION BLASTING COMBUSTION ENGINES COSMONAUTICS ENGINE PLANTS IN GENERAL EQUIPMENT FOR FITTING IN OR TO AIRCRAFT FLYING SUITS 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 PARACHUTES PERFORMING OPERATIONS STEAM ENGINES TRANSPORTING WEAPONS
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Beschreibung
Zusammenfassung:	A gas turbine engine is provided with a translatable cowl and a cascade structure which is nested within the translatable portion of the cowl. The cascade structure comprises C shaped sections which are exposed upon translation of a portion of the cowl. The C shaped sections are capable of rotation about an axis parallel to the longitudinal axis of the engine thus allowing acces to the core of the engine.