A segmented theoretical method was proposed to derive the temperature and stress distributions of a variable thickness turbine disk under given heating energy on the inner and outer rims

and the correlation between the energy distributions presented by the energy transfer coefficient

and the temperature/stress distributions of the turbine disk was established. By applying the correlation to an aero-engine low pressure turbine disk and comparing the temperature and stress distributions with those obtained from numerical simulation

the results from these two methods show a good agreement; the relative deviations of the temperature and stress distributions are no more than 2% and 13%

respectively; under constant boundary heat flow condition

the temperature of the inner rim increases while that of the outer rim decreases; both the overall equivalent stress level and the maximum equivalent stress of the turbine disk decline with the increase of the energy transfer coefficient. The above results validate that the correlation between the energy and stress distributions obtained from the segmented theoretical method proposed is feasible and correct.