GAS TURBINE ENGINE FAN

There is disclosed a fan blade (25) for a gas turbine engine (10), comprising a hub end (44) for attachment to a rotor hub (42) in use. The blade extends from the hub end towards a tip end (46) so as to define a blade span dimension (48). The blade further has a leading edge (52) and a trailing edge...

Ausführliche Beschreibung

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Bibliographische Detailangaben
1. Verfasser:	Baralon, Stephane
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	BLASTING ENGINE PLANTS IN GENERAL HEATING LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES WEAPONS
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Beschreibung
Zusammenfassung:	There is disclosed a fan blade (25) for a gas turbine engine (10), comprising a hub end (44) for attachment to a rotor hub (42) in use. The blade extends from the hub end towards a tip end (46) so as to define a blade span dimension (48). The blade further has a leading edge (52) and a trailing edge (54), a chord (64) for a sectional profile of the blade being a straight line joining the leading and trailing edges within the sectional profile. A relative difference in angle between a chord in a mid-span region of the blade and a chord in the vicinity of the tip end of the blade is greater than or equal to 20°.