Turbine rotor blade for gas turbine engine

A rotor blade for a gas turbine engine comprises 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 a...

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Bibliographische Detailangaben
1. Verfasser:	HARVEY, NEIL WILLIAM
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:	A rotor blade for a gas turbine engine comprises 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.