Lufthansa Technik Ag

Stefan Kuntzagk

Jan Oke Peters

Thomas Maria Gartner

Tim Luebcke

Joachim Schoen

Oliver Winter

Joachim Schon

Thomas Gartner

Tim Lübcke

A device for recontouring a gas turbine blade includes: a holding device having at least one cutting tool; and a guide configured to guide the cutting tool along a leading edge of the gas turbine blade. The cutting tool is configured to remove material from the gas turbine blade using a rotational movement about an axis of rotation. The axis of rotation forms an angle together with a chord of the gas turbine blade in a profile section plane, which extends perpendicularly to a radial extent of the gas turbine blade, and the angle is less than 45&#xb0;.

Device and method for re-contouring a gas turbine blade

A flow element for fluidic contact with a hot gas flow inside an aircraft engine includes: a base material, which has a hot gas surface that faces the gas flow and a remote surface that is remote from the gas flow, the base material being completely surrounded by a chroming layer on the hot gas surface and on the remote surface; an adhesive layer on the chroming layer in first portions; an alitising layer, the alitising layer being arranged on the adhesive layer in the first portions; and a thermal barrier layer being arranged on the alitising layer in the first portions. The alitising layer is arranged on the chroming layer in second portions that do not have an adhesive layer, the chroming layer and the alitising layer forming a chroming-alitising layer in the second portions.

Flow element and method for coating a flow element

Growing community of inventors

Hamburg, Germany

Stefan Kuntzagk