GAS TURBINE ENGINE

A gas turbine engine (20;100;120;140;150;170) comprises a fan rotor (42;174) having fan blades (98;134) received within an outer nacelle (94;122;145;172), and the outer nacelle (94...172) having an inner surface (132;151). A distance (L) is defined between an axial outer end (B) of the nacelle (94.....

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Bibliographische Detailangaben
Hauptverfasser:	MURPHY, Michael Joseph, SCHWARZ, Frederick M
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 gas turbine engine (20;100;120;140;150;170) comprises a fan rotor (42;174) having fan blades (98;134) received within an outer nacelle (94;122;145;172), and the outer nacelle (94...172) having an inner surface (132;151). A distance (L) is defined between an axial outer end (B) of the nacelle (94...172), and a leading edge (102) of the fan blades (98;134). An anti-icing treatment is provided to an inner periphery of the nacelle (94...172) over at least 75% of the distance (L) along the inner periphery of the nacelle (94...172).