Problem 2 Known An Afterburner Is Added To The Turbojet In Problem 1 Find Determine The Velocity At The Nozzle Exit 1 (47.44 KiB) Viewed 32 times
Problem #2 Known: An afterburner is added to the turbojet in Problem #1. FIND: Determine the velocity at the nozzle exit. SCHEMANC 6 GIVEN DATE: 163.4 kPa T 1300K Zain - 26 kPa Ty' = 1300K
Problem #1 Known: The performance of a turbojet engine is shown below. Assume combustion occurs at constant pressure. Heat addition in the combustor is based on an air-standard analysis. EIND: Determine ca) the pressures and temperatures at each principal State, (b) the rate of heat addition, and cc) the velocity at the norz'le exit. SCHEMATICS GIVEN DATA: =1400k TI Ne=0.90 १०. 45 28 P3/P.11 5 Diffuser 26 kPa S Ps= 26 kPa Ta=230k Pa = 26 l. Pa va - 220 m/s 25 kgs 4
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