The maximum temperature that the turbine blades can withstand limits the performance of a turbojet engine. This temperature, in turn, is controlled by the temperature of the combustion products exiting the combustor. Determine the minimum air–fuel ratio that can be supplied to a turbojet engine such that the combustor outlet temperature does not exceed 1200 K (1700 F) when the air enters at 400 K. Assume the fuel is C₁₀H₂₂ and enters the combustor at 298 K. Also assume the usual simplified composition of air.

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Aircraft turbine blades. Photograph courtesy of NASA.