GEARED GAS TURBINE ENGINE

A gas turbine engine comprises, in axial flow sequence, a fan section, a compressor section, and a turbine section. The fan section has a fan that is enclosed by a fan casing. The turbine section is operatively connected to the compressor section. The gas turbine engine also comprises a planetary ge...

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Bibliographische Detailangaben
Hauptverfasser:	O'Hanrahan, Tim, Stretton, Richard
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 JET-PROPULSION PLANTS LIGHTING MECHANICAL ENGINEERING WEAPONS
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Beschreibung
Zusammenfassung:	A gas turbine engine comprises, in axial flow sequence, a fan section, a compressor section, and a turbine section. The fan section has a fan that is enclosed by a fan casing. The turbine section is operatively connected to the compressor section. The gas turbine engine also comprises a planetary gear train, and a core engine casing. The gear train has a ratio of greater than approximately 3.0, with an input to the gear train being operatively connected to the compressor section, and an output from the gear train being operatively connected to the fan. The core engine casing encloses the compressor section and the turbine section. The fan has a diameter F, and the core engine casing has a diameter C. The core engine casing diameter C varies along an axial length of the core engine casing, and a ratio (C/F) of the core engine casing diameter C to the fan diameter F is within the range 0.2