Nose cone for an airplane turbine engine with integrated balancing ring

The fan (1) has an annular balancing flange (34) coupled in rotation with a fan disk (4) along a longitudinal rotational axis (2), and including weight fixation holes (24) spaced circumferentially from one another. Balancing weights i.e. balancing screws (26), are fixed on the flange by the holes. T...

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Bibliographische Detailangaben
Hauptverfasser:	Goga, Jean-Luc, Christian, Yvon, Belmonte, Olivier
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 ENGINE PLANTS IN GENERAL GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE 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 WEAPONS
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Beschreibung
Zusammenfassung:	The fan (1) has an annular balancing flange (34) coupled in rotation with a fan disk (4) along a longitudinal rotational axis (2), and including weight fixation holes (24) spaced circumferentially from one another. Balancing weights i.e. balancing screws (26), are fixed on the flange by the holes. The flange is arranged inside an inlet cone (20) in a manner that the holes are isolated from a jet (22) of a turbomachine i.e. jet engine, of an aircraft. A blade retaining ring (16) axially retains fan blades (6) with respect to the disk. The ring and the flange are formed of a single piece.