Abstract: An arrangement of a plurality of cooling channels within a turbine blade conveys cooling fluid, wherein the cooling channels lead through the turbine blade, which has a blade root, a blade tip, a leading edge, and a trailing edge, to one or more cooling-fluid outlets, wherein the cooling channels are connected to each other at selected locations and extend separately from each other in other regions in such a way that, in the event of damage to the turbine blade in the region of one cooling channel, the cooling by the other cooling channels remains largely unimpaired, wherein at least one cooling channel begins in a region near the leading edge and near the blade root and leads as a diagonal channel through the turbine blade into a region near the trailing edge and near the blade tip.

Abstract: A method for stabilizing the flame of a premixing burner, comprising a reaction chamber containing a fluid is provided. The method includes injecting an air-fuel mixture into the reaction chamber at a speed that is different from that of the fluid present in the reaction chamber, adjusting the speed such that vortices form at the boundary between the air-fuel mixture and the surrounding fluid. A premixing burner including a reaction chamber and at least one premixing spray nozzle opening into the reaction chamber is also provided. The premixing burner injects an air-fuel mixture into the reaction chamber at a speed that is different from that of the surrounding fluid, the speed being adjusted such that vortices from at the boundary between the air-fuel mixture and the surrounding fluid.