GAS TURBINE INLET

An inlet for a gas turbine engine having an inlet lip and an inlet barrel, the inlet lip having a highlight defining a boundary between inner and outer surfaces of the inlet lip. The inlet barrel has a forwardly extending flange that is joined to the inlet lip by overlapping surfaces. The flange int...

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Bibliographische Detailangaben
Hauptverfasser:	KUBISCH THOMAS, TODOROVIC PREDRAG
Format:	Patent
Sprache:	eng
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:	An inlet for a gas turbine engine having an inlet lip and an inlet barrel, the inlet lip having a highlight defining a boundary between inner and outer surfaces of the inlet lip. The inlet barrel has a forwardly extending flange that is joined to the inlet lip by overlapping surfaces. The flange interface surface has a conus angle that is divergent from the highlight axis.