Abstract: A multi-stage axial-flow turbine structure where in order to reduce the energy content of the gaseous working medium leaving the last moving blade row in comparison to the available heat drop, the flow discharge cross-section area from the last moving row, compared to the flow discharge cross-section area of the penultimate moving row, is made larger by some 10 to 40 % than would correspond to the ratio of the increase in volume of the working medium from the penultimate to the last moving blade now. This is accomplished, for example, by increasing the ratio of the passage width to blade pitch and/or by increasing the annular flow area, this ratio being varied over the length of the blades of the last row in order to obtain a uniform velocity profile in the axial and tangential directions.