Gas turbine engine with counter-rotating fan blades

An exemplary embodiment of a FLADE (fan on blade) counter-rotating fan aircraft gas turbine engine includes at least one row of FLADE fan blades (5) disposed radially outwardly of and drivingly connected to one of axially spaced-apart first and second counter-rotatable fans (130 and 132). A core eng...

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Bibliographische Detailangaben
Hauptverfasser:	GIFFIN,ROLLIN GEORGE, III, JOHNSON, JAMES EDWARD
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TOTRANSPORTATION COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ENGINE PLANTS IN GENERAL GAS-TURBINE PLANTS GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS INDEXING SCHEME FOR ASPECTS RELATING TONON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES ORJET-PROPULSION PLANTS INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUSSUBCLASSES OF CLASSES F01-F04 JET-PROPULSION PLANTS LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES NON-POSITIVE DISPLACEMENT PUMPS POSITIVE DISPLACEMENT MACHINES FOR LIQUIDS PUMPS FOR LIQUIDS OR ELASTIC FLUIDS STEAM ENGINES TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINSTCLIMATE CHANGE WEAPONS
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Beschreibung
Zusammenfassung:	An exemplary embodiment of a FLADE (fan on blade) counter-rotating fan aircraft gas turbine engine includes at least one row of FLADE fan blades (5) disposed radially outwardly of and drivingly connected to one of axially spaced-apart first and second counter-rotatable fans (130 and 132). A core engine (18) located downstream and axially aft of the first and second counter-rotatable fans (130 and 132) is circumscribed by a fan bypass duct (40) downstream and axially aft of the first and second counter-rotatable fans (130 and 132). The row of FLADE fan blades (5) radially extend across a FLADE duct (3) circumscribed about the first and second counter-rotatable fans (130 and 132) and the fan bypass duct (40). A second low pressure turbine (21) is drivingly connected to the first counter-rotatable fan (130) and a first low pressure turbine (19) is drivingly connected to the second counter-rotatable fan (132).