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MAE112FinalExam_2009

MAE112FinalExam_2009 - MAE 112 PROPULSION FINAL EXAM Do all...

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1 MAE 112 PROPULSION FINAL EXAM March 19, 2009 Do all four problems in 120 minutes. Books, notes and calculators can be used freely. 1. An afterburner has an exhaust temperature of 3000 R into a nozzle and operates at 4.5 atmospheres of pressure. The afterburner is immediately downstream of the turbine in a turbojet engine. For every mole of liquid octane fuel C 8 H 18 added to the afterburner, the inflowing mixture of product gases and excess air has 16, 18, 15, and 150.4 moles, respectively, of CO 2 , H 2 O, O 2 , and N 2 . The liquid fuel is introduced to afterburner at the initial temperature of 515 R with a heating value Q=19135 Btu/lbm which accounts for vaporization heat. Neglect dissociation. Assume the flow through the afterburner has c p = 0.33 Btu/lbm-R and a ratio of specific heats equal to 1.25, with values of c p = 0.30 Btu/lbm-R and a ratio of specific heats equal to 1.30 for the turbine. The polytropic efficiency of the turbine is 0.96 and the afterburner efficiency is 0.99. The temperature entering the turbine is 2600 o R.

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MAE112FinalExam_2009 - MAE 112 PROPULSION FINAL EXAM Do all...

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