Calculation of the temperature distribution in the turbine rotor of the axial gas turbine engine is an essential preliminary to a meaningful calculation of the stress distribution and the prediction of related life of the various rotor elements. Where the turbine blades are uncooled, the element of chief concern is the turbine disk, with respect to achieving acceptable life. The art of performing a multistage axial gas turbine rotor assembly temperature distribution analysis is reviewed in detail with particular emphasis on choice of heat transfer correlations and boundary conditions in the steady state. Modification of the thermal model to yield transient temperature results is discussed briefly. Comparison of analytical results with some recent engine disk temperature measurements is presented.

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