Abstract: A processing area of a structural component, such as a gas turbine component, is heated by irradiation with several laser sources prior to and/or during and/or after carrying out a processing such as a deposit welding or machining of the component on the processing area. For the heating, each laser source directs a respective energy beam onto the processing area, which respectively produces an energy spot on the processing area. The respective positions of the energy spots are static or quasi-static on the processing area. The energy spots jointly heat the processing area.

Abstract: The invention relates to a semi-finished product for producing a repaired blade for a gas turbine. Said semi-finished product comprises a first part (10) and a second part (12) firmly connected to the first part (10), the first part (10) having at least one recess (18) into which the second part (12) projects. The invention also relates to a method for repairing a blade of a gas turbine. Said method comprises the following steps: applying a first part (10) and making a recess (18), especially a groove (18) into said first part (10); applying a second part (12); inserting the second part (12) into the first part (10) in such a manner that the second part (12) or at least one section of the second part (12) projects into the recess (18) or groove (18); and connecting, especially welding, the first part (10) to the second part (12) in such a manner that the first part (10) and the second part (12) are non-detachably interconnected after said connection.

Abstract: An apparatus for the heat treatment of integral rotors of gas turbines is disclosed. The apparatus includes a closable working space which can be evacuated or filled with inert gas, a heat source, a distance-measuring instrument, and a pyrometer. A method for diminishing and/or for eliminating internal stresses which are introduced into a component through welding is also disclosed.

Abstract: The invention relates to a method for heating a machining area of a structural component, particularly a gas turbine component, prior to and/or during and/or after a machining or processing of the component on the machining area. According to the invention, the machining area (13) is irradiated by several laser sources for heating, wherein each laser source directs an energy beam onto the machining area such that each laser source respectively produces an energy spot (15) on the machining area (13), which jointly heat the machining area, and wherein each of the laser sources produces a static or quasi-static energy spot (15) on the machining area such that the position of the respective energy spot (15) on the machining area (13) is static or quasi-static.

Abstract: A repair process for blades of turboengines damaged in the head or edge regions in which the damaged regions are first separated to leave an undamaged blade stump with an exposed, repair surface. The repair surface of the blade stump is prepared for butt welding and a repair plate of constant thickness which exceeds the maximum profile height of the blade by more than 50% is provided with a front surface adapted to the repair surface. This front surface of the repair plate is abutted against the repair surface and the blade stump and the repair blade are then butt welded. The weld joint and the repair plate are machined to the profile contour of the blade stump and to the desired blade profile. This process is used for the repair of blades of integral rotor disks of turboengines, particularly for blades of integral compressor impellers.