Mtu Aero Engines Ag

Lars Schellhorn

Frank Stiehler

Andre Dr Werner

A moving blade for a turbine or compressor stage of a gas turbine is provided, including a vane () and a radially outer shroud (), for at least one contour point (P) of an outer contour of a profile cross section (P) of the vane at a radial outer gas channel boundary, the wall thickness of the shroud at at least one edge point (P) of the shroud, whose connecting line (V), including the contour point with a normal (N), which is perpendicular to the outer contour of the profile cross section in the contour point, encloses an angle (&#x3c3;), which is no more than 5&#xb0;, is less than a wall thickness of the shroud at the contour point, the wall thickness of the shroud decreasing strictly monotonously along the connecting line.

Gas turbine moving blade

A method for manufacturing a blade or vane assembly having at least one hollow airfoil () for a gas turbine, profile sections (A, B, C) of this airfoil being configured (S) on the basis of a predetermined desired torsion of the airfoil, and the airfoil being manufactured (S) on the basis of the configured profile sections using an additive manufacturing process (S).

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Saalfeld, Germany

Lars Schellhorn