Gas turbine blade comprising bended leading and trailing edges

摘要

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 airfoil depending on the span. The invention is characterized in that the axial chord length increases at least from 80% span to 100% span.