Rotor blade with air flow passages

A rotor blade 2 for a turbo machine, such as a gas turbine engine, comprising an aerofoil 6 having pressure and suction surfaces 8,10, leading and trailing edges 12, 14, and an array of passages 20 at a tip region 18 of the aerofoil, where the passages extend from the pressure surface to the suction...

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser:	STEPHANE MICHEL MARCEL BARALON, NEIL WILLIAM HARVEY
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 NON-POSITIVE DISPLACEMENT PUMPS POSITIVE DISPLACEMENT MACHINES FOR LIQUIDS PUMPS FOR LIQUIDS OR ELASTIC FLUIDS STEAM ENGINES WEAPONS
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Beschreibung
Zusammenfassung:	A rotor blade 2 for a turbo machine, such as a gas turbine engine, comprising an aerofoil 6 having pressure and suction surfaces 8,10, leading and trailing edges 12, 14, and an array of passages 20 at a tip region 18 of the aerofoil, where the passages extend from the pressure surface to the suction surface and are disposed so that the array creates a jet of gas issuing from the suction surface that is inclined outwardly from the suction surface and towards the tip in the direction from the leading edge to the trailing edge. Preferably the passage outlets are situated a distance of between 1% and 25% of the span of the aerofoil from the tip and not more than a distance of 25% of the chord of the aerofoil from the leading edge. A rotor assembly is also claimed.