Abstract: Embodiments relate to a gas turbine blade for an aircraft engine, the gas turbine blade having a flow leading edge, a flow trailing edge, a suction side, and a pressure side, where the suction side and pressure side extend from the flow leading edge to the flow trailing edge, wherein the gas turbine blade has a damping layer on the flow leading edge and the damping layer comprising at least one matrix material and particles held in position by this matrix material. Further embodiments relate to a method of coating a gas turbine blade and a gas turbine incorporating a plurality of gas turbine blades in accordance with embodiments of the invention.

Abstract: Method for repairing a gas turbine component, which at least at the spot to be repaired consists of a ceramic composite material, where an energy beam locally heats the gas turbine component in a zone, and where one or more auxiliary materials and optionally fibers and/or particles are fed to this zone, wherein a ceramic is generated in the melting zone through the one or more auxiliary materials, and, optionally, the one or more auxiliary materials together with the fibers and/or particles forms a ceramic composite material.

Abstract: Device (1) for recontouring a gas turbine blade (2), comprising: at least one support (6a, 6b) configured to rest on an edge (3a) of the gas turbine blade (2) during the recontouring, at least one side bearing (5a, 5b) configured to rest on the suction- and/or pressure side (3b, 3c) of the gas turbine blade (2) in a lateral direction (7) during the recontouring, a machining unit (4) via which the gas turbine blade (2) is cutting machined in a machining direction (8) along the edge (3a), wherein the machining unit (4) can be displaced perpendicularly to the machining direction (8).

Abstract: A method for recontouring a blade of a gas turbine includes systematically melting a portion of a leading edge of the blade using an energy beam so as to form a new contour of hardened material substantially without incorporating additional material.

Abstract: A device for recontouring a gas turbine blade includes at least one support configured to rest on an edge of the gas turbine blade during the recontouring, at least one side bearing configured to rest on an intake side or an outlet side of the gas turbine blade during the recontouring and a machining unit for machining the gas turbine blade. The machining unit is configured to fuse at least one partial area of the edge of the gas turbine blade using a beam of energy that is targeted such that material of the blade solidifies into a new contour, substantially without the addition of supplementary material.

Abstract: Device (1) for recontouring a gas turbine blade (2), comprising: at least one support (6a, 6b) configured to rest on an edge (3a) of the gas turbine blade (2) during the recontouring, at least one side bearing (5a, 5b) configured to rest on the suction- and/or pressure side (3b, 3c) of the gas turbine blade (2) in a lateral direction (7) during the recontouring, a machining unit (4) via which the gas turbine blade (2) is cutting machined in a machining direction (8) along the edge (3a), wherein the machining unit (4) can be displaced perpendicularly to the machining direction (8).

Abstract: Embodiments relate to a gas turbine blade for an aircraft engine, the gas turbine blade having a flow leading edge, a flow trailing edge, a suction side, and a pressure side, where the suction side and pressure side extend from the flow leading edge to the flow trailing edge, wherein the gas turbine blade has a damping layer on the flow leading edge and the damping layer comprising at least one matrix material and particles held in position by this matrix material. Further embodiments relate to a method of coating a gas turbine blade and a gas turbine incorporating a plurality of gas turbine blades in accordance with embodiments of the invention.

Abstract: Method for repairing a gas turbine component, which at least at the spot to be repaired consists of a ceramic composite material, where an energy beam locally heats the gas turbine component in a zone, and where one or more auxiliary materials and optionally fibers and/or particles are fed to this zone, wherein a ceramic is generated in the melting zone through the one or more auxiliary materials, and, optionally, the one or more auxiliary materials together with the fibers and/or particles forms a ceramic composite material.

Abstract: A method for recontouring a blade of a gas turbine includes systematically melting a portion of a leading edge of the blade using an energy beam so as to form a new contour of hardened material substantially without incorporating additional material.

Abstract: A method for laser welding super alloys is disclosed. The power of the laser (12) is controlled depending on the temperature of the welding bath and a device (10) for laser welding a super alloy, including a laser beam source (12), a process controller (30), a temperature recording unit (28) and a feed device (24) for additional materials, characterized in that the process controller (30) comprises a regulator (34), connected to the temperature recording unit (28) and the laser source (12).

Abstract: A method is provided for heating components before and/or during a further processing thereof. At least one laser device is used as energy source for heating.