Turbine rotor blade for gas turbine engine

A rotor blade for a gas turbine engine includes a blade root ( 3 ) and an aerofoil projecting therefrom, the aerofoil having a leading edge and a trailing edge ( 5 ), a generally concave pressure surface ( 2 ) and a generally convex suction surface ( 1 ). The aerofoil shape of the blade varies in se...

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Bibliographische Detailangaben
1. Verfasser:	HARVEY NEIL W
Format:	Patent
Sprache:	eng
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:	A rotor blade for a gas turbine engine includes a blade root ( 3 ) and an aerofoil projecting therefrom, the aerofoil having a leading edge and a trailing edge ( 5 ), a generally concave pressure surface ( 2 ) and a generally convex suction surface ( 1 ). The aerofoil shape of the blade varies in section along the length thereof such that: the chord-wise convex curvature of the rear suction surface decreases towards the tip ( 4 ) of the blade; the convex curvature of the early to mid suction surface increases towards the tip; the stagger of the aerofoil section increases towards the tip; and the trailing edge ( 5 ) is a straight line.