In order to illustrate optimization possibilities, the cooled axial turbine stage has been investigated regarding aerothermodynamics. Aims of the study are: (a) to estimate the range of the aspect ratio in which the aerothermodynamic efficiency, under comparable conditions, is not less than 0.2 percent under the best value in order to acquire tolerances for the best possible blading design when considering other design and aspects; (b) to acquire the relationship of the turbine loss coefficients and efficiencies to the absolute size of the flow channels, i.e. (also) to the hot gas flowrate. This is important for fair comparison of smaller and larger machines as well as for realistic judgments and prognosis pertaining especially to small units.