GAS TURBINE ENGINE WITH IDLE THRUST RATIO

A gas turbine engine (120) includes a fan section (122) comprising a fan having a plurality of fan blades (142) and an outer housing (115) surrounding the fan blades (142) to establish a bypass duct (113), a geared architecture (148), a first spool (13)) including a first shaft (14) that interconnec...

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Bibliographische Detailangaben
Hauptverfasser:	COLLOPY, Gary, TURGUT, Ozhan, PIXTON, Stephen G
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 (120) includes a fan section (122) comprising a fan having a plurality of fan blades (142) and an outer housing (115) surrounding the fan blades (142) to establish a bypass duct (113), a geared architecture (148), a first spool (13)) including a first shaft (14) that interconnects a first compressor (144) and a fan drive turbine (146) that drives the fan through the geared architecture (148). A thrust ratio defined as a ratio of the amount of thrust at ground idle divided by the amount of thrust at maximum takeoff is less than or equal to 0.050.