Consider the turbojet combustor described in Example 12.8. Determine the temperature of the combustion products exiting the combustor if the air–fuel ratio is reduced to 50:1.

Example 12.8

Consider a turbo-jet-powered aircraft flying at 200 m/s at 6000-m altitude. At these conditions, air enters the combustor at 349.8 kPa and 449.2 K. The fuel, liquid n-dodecane (C₁₂H₂₆), is sprayed into the combustor at 298 K to provide an overall air-fuel ratio of 75:1. The corresponding equivalence ratio is Φ = 0.1988.

Determine the temperature of the combustion products at the combustor exit. Also determine the constant-pressure specific heat of the product mixture.

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Air Fuel T 1 1 Products