Unformatted text preview: properties at various states. For a plane flying at 100 m/s: a. Draw the T-s diagrams for this jet engine (including the afterburner). b. Find the total heat added in the afterburner, per mass air (in kJ/kg) c. Find the nozzle exit velocity (in m/s), assuming the gases are fully expanded to atmospheric pressure in the nozzle, and assuming the hot gases enter the nozzle at zero velocity. Neglect changes in ke except in the nozzle. Also find the exit velocity without afterburning. diffuser compressor T 2 = -33 C P 2 = 35 kPa 1 2 3 Q 34 P 3 = 571.55 kPa T 4 = 1500 K 4 5 Q 56 6 7 afterburner nozzle turbine combustor T 6 = 1500 . . T 1 = -37 C P 1 = 32.84 kPA...
View Full Document
- Fall '08
- Turbofan, Gas turbine, Afterburner, turbine exhaust gases, nozzle exit velocity