Gas turbine blade comprising bended leading and trailing edges

The invention refers to a a gas turbine blade comprising an airfoil extending in radial direction from a blade root to a blade tip, defining a span ranging from 0% at the blade root to 100% at the blade tip, and extending in axial direction from a leading edge to a trailing edge, which limit a chord...

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser:	NEUBRAND, FABIAN, HOFMANN, WILLY HEINZ
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:	The invention refers to a a gas turbine blade comprising an airfoil extending in radial direction from a blade root to a blade tip, defining a span ranging from 0% at the blade root to 100% at the blade tip, and extending in axial direction from a leading edge to a trailing edge, which limit a chord with an axial chord length defined by an axial length of a straight line connecting the leading edge and trailing edge of the air-foil depending on the span. The invention is characterized in that the axial chord length increases at least from 80% span to 100% span.