Abstract: A system for simulation of a composite beam is disclosed. The system can comprise a memory storing executable instructions and one or more processors coupled to the memory to execute the executable instructions. The one or more processors can be configured to generate a representation of the original beam pattern transmitted via a propagation of the composite beam, to invoke a propagation model that represents a distortion for the propagation of the composite beam, and to determine a representation of a distorted beam pattern based on the propagation model and on the representation of the original beam pattern transmitted via the propagation.

Abstract: A method for the simulation of a propagation of electromagnetic beams, in particular light beams, is revealed, comprising the following steps of parametric specification of a first beam relative to a first boundary layer, specification of a first material into which the first beam should propagate after the first boundary layer, and determination of a reflection and/or transmission of the first beam relative to the first boundary layer on the basis of the first material and on the basis of a first model, wherein the first model comprises one or more functions which associate one or more reflection and/or transmission parameters with the first beam, and wherein the reflection and/or transmission parameter(s) associated with the first beam via the functions are determined.

Abstract: A method for removing the coating from a gas turbine component, namely for the complete or partial removal of a multilayer wear protection coating from the surface of the gas turbine component, the wear protection coating having at least one relatively hard ceramic layer and at least one relatively soft metallic layer, wherein, in order to remove the multilayer wear protection coating, the gas turbine component is alternately positioned in two different chemical baths, a first bath being used exclusively for the removal of each relatively hard ceramic layer, and a second bath being used exclusively for the removal of each relatively soft metallic layer of the wear protection coating.

Abstract: A method for removing the coating from a gas turbine component, namely for the complete or partial removal of a multilayer wear protection coating from the surface of the gas turbine component, the wear protection coating having at least one relatively hard ceramic layer and at least one relatively soft metallic layer, wherein, in order to remove the multilayer wear protection coating, the gas turbine component is alternately positioned in two different chemical baths, a first bath being used exclusively for the removal of each relatively hard ceramic layer, and a second bath being used exclusively for the removal of each relatively soft metallic layer of the wear protection coating.

Abstract: A facility for the selective separation of a stream of mixed bulk materials made up of objects of different densities and possibly different sizes comprising a sorting device having at least one conveyor belt on which the stream of mixed bulk materials to be selected is conveyed; and at least one nozzle by means of which compressed air can be blown transversely to the conveying direction and against the stream of mixed bulk materials lying on the conveyor belt, including at least one separating element and at least two collection containers, one of which is placed laterally approximately opposite the nozzle and the other of which is placed in the end region of the conveyor belt.