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Question: a combustor is designed to run on jeta fuel and...

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A combustor is designed to run on Jet-A fuel and 2.5 times as much air as needed to burn the fuel (also known as 150% excess

A combustor is designed to run on Jet-A fuel and 2.5 times as much air as needed to bum the fuel (also known as 150% excess air). For this problem, assume Jet-A (which is a mixture of hydrocarbon fuels) has a carbon: hydrogen ratio of 10: 22 (i.e., you could write its "chemical formula as C_10 H_22. a) What is the fuel-air ratio (f = m_f/m_a) and equivalence ratio (phi) of the combustor at these conditions. b) Determine the composition (mole fractions AND mass fractions) of the product gases for this fuel lean mixture, assuming the products are composed ONLY of H_2O, CO_2, O_2 and N_2. c) What is the exit temperature for the combustor if the reactants enter the combustor at 800 K and 30 atm AND assuming that the combustor is adiabatic. This temperature is known as the adiabatic flame temperature. (Note, the inlet conditions given here are typical for the air entering a modem gas turbine combustor after passing through a compressor at take-off conditions.) Obtain necessary gas properties ONLY from the table below - no other sources.

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