A Rapid Approximate Method of Determining Axial-Flow Turbine Disk and Blade Temperatures

A method of determining the temperature profile of a single-stage axial-flow turbine disk with uncooled blades is presented. The blade temperature is also estimated. Information required for the solution is: the gas properties and velocity entering the rotor, the blade and disk geometry, the blade fastening geometry, and the disk-to-shaft attachment geometry. Impingement disk cooling may be used. The temperature of the shaft at a point near the journal bearing mutt be assumed, but it is shown that this assumption is not critical. A stepwise numerical solution, suitable for either hand calculation or computer programming, is employed. The method may be extended to multi-stage turbines. A typical example is given and the effect of changing the radius of injection of the disk cooling air is shown.