HIGH BYPASS-RATIO TURBOFAN JET ENGINE

PROBLEM TO BE SOLVED: To provide a turbofan jet engine which is capable of increasing a bypass ratio without increasing a fan diameter and of reducing air resistance acting on the engine. SOLUTION: In a high-bypass ratio turbofan jet engine, front-fan flow ducts 20a, 20b for discharging compressed a...

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Bibliographische Detailangaben
Hauptverfasser:	FUJIWARA HITOSHI, YANAGI RYOJI
Format:	Patent
Sprache:	eng
Schlagworte:	AEROPLANES AIR INTAKES FOR JET-PROPULSION PLANTS AIRCRAFT ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT AVIATION BLASTING CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TOTRANSPORTATION COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS COSMONAUTICS EQUIPMENT FOR FITTING IN OR TO AIRCRAFT FLYING SUITS GAS-TURBINE PLANTS GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS HEATING HELICOPTERS 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 MECHANICAL ENGINEERING PARACHUTES PERFORMING OPERATIONS TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINSTCLIMATE CHANGE TRANSPORTING WEAPONS
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Beschreibung
Zusammenfassung:	PROBLEM TO BE SOLVED: To provide a turbofan jet engine which is capable of increasing a bypass ratio without increasing a fan diameter and of reducing air resistance acting on the engine. SOLUTION: In a high-bypass ratio turbofan jet engine, front-fan flow ducts 20a, 20b for discharging compressed air compressed by a front fan 10 to the open air, and aft-fan flow ducts 50a, 50b for introducing air to an aft-fan 40 are disposed so as to change cross-sectional shapes thereof by rorating around a core engine 30 in a counterclockwise direction, so that the geometrical relationship between the front-fan flow ducts 20a, 20b and the aft-fan flow ducts 50a, 50b is inverted, in a section 1 immediately posterior to the front-fan 10 and a section 11 immediately anterior to the aft-fan 40. COPYRIGHT: (C)2009,JPO&INPIT