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RESULTS of an investigation to measure the operating temperatures in a disc of a typical gas turbine engine are presented here. These temperature data were used to determine operating stresses and their implications on disc bursting, rim cracking, and inner-region cooling. In turbine blades the major unknowns are reported to be temperatures and vibrational stresses during operation. Results are shown of investigations to measure temperature distributions and vibrational stresses in a typical gas-turbine engine. The temperatures and centrifugal stresses were such as to allow little vibratory stress. Measurements showed that appreciable vibration was present, however, excited mainly by the nozzle vanes and the combustion chambers.