GAS TURBINE ENGINE ROTOR BLADE WITH A LOCAL PRESSURE SIDE BLADE TIP LEAN

A rotor blade (70) of a gas turbine engine (20) includes a pressure side (88), and a suction side (90) opposite the pressure side and defining a rotor blade profile therebetween, the pressure side and the suction side each extending from a blade root (72) to a blade tip (74). The rotor blade defines...

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Bibliographische Detailangaben
1. Verfasser:	EVANS, Simon W
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 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 (70) of a gas turbine engine (20) includes a pressure side (88), and a suction side (90) opposite the pressure side and defining a rotor blade profile therebetween, the pressure side and the suction side each extending from a blade root (72) to a blade tip (74). The rotor blade defines a cross-sectional median line (92) midway between the pressure side and the suction side. The cross-sectional median line extends in a generally radial direction from the blade root to a lean point (96) between the blade root and the blade tip. The cross-sectional median line extends off of radial from the lean point to the blade tip, defining a lean of the rotor blade between the lean point and the blade tip.