LAYERED ICE LINER

A liner assembly for lining of a gas turbine engine includes a honeycomb core having at least two axially adjacent segments, including a forward segment and an aft segment. An impact resistant layer is disposed against and radially inward of the honeycomb forward segment. A radially interior layer,...

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Bibliographische Detailangaben
Hauptverfasser:	CLARKSON, Steven, BERGETHON, Richard B
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MECHANICAL ENGINEERING WEAPONS
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Beschreibung
Zusammenfassung:	A liner assembly for lining of a gas turbine engine includes a honeycomb core having at least two axially adjacent segments, including a forward segment and an aft segment. An impact resistant layer is disposed against and radially inward of the honeycomb forward segment. A radially interior layer, defining a relatively substantially uninterrupted flowpath over at least a portion of the impact resistant layer and the aft segment, extends against and radially interior of both the impact resistant layer and the honeycomb aft segment.