2. An afterburning Turbo Jet engine operates at (same question as Q1 of HW2 but with different A. and p) M. -1.5, po 10

Post by **answerhappygod** » Mon May 09, 2022 9:15 am

: 2 An Afterburning Turbo Jet Engine Operates At Same Question As Q1 Of Hw2 But With Different A And P M 1 5 Po 10 1 (44.98 KiB) Viewed 18 times

: 2 An Afterburning Turbo Jet Engine Operates At Same Question As Q1 Of Hw2 But With Different A And P M 1 5 Po 10 2 (41.68 KiB) Viewed 18 times

2. An afterburning Turbo Jet engine operates at (same question as Q1 of HW2 but with different A. and p) M. -1.5, po 10 kPa, To -25°C, Y - 14.1.004 kJ/kg K. y) = 1.33, C = 1.156 kJ/kg K. Ta = 0.95, = 15, 4 = 0.9, 1 = 7.0, p = 0,9, To = 0,95, họa = 42000 kJ/kg, 6 = 0.82, me = 0.98, tus -10.0, hrkas - 42000 kJ/kg, mas = 0.95, TAD = 0.93. Yas - 1.3, CAB 1.243 kJ/kg K. 11 (2-1) Calculate below (A) assuming isentropic nozzle flow (- 1) and perfect nozzle pressure recovery (popo) without knowledge in nozzle choking A-la) Total pressures and temperatures at each inlet and outlet of component throughout the engine A-(b) Exit vclocity A-(c) Specific thrust A-d) Thrust specific fuel consumption A-(e) Thermal and propulsive efficiencies (2-2) Repeat the same (B) assuming isentropic nozzle flow (za - 1) but considering potential choked flow in the nozzle and compare the results with (A) B-a) Total pressures and temperatures at each inlet and outlet of component throughout the engine B-b) Exit velocity B-C) Specific thrust B-d) Thrust specific fuel consumption B-te) Thermal and propulsive efficiencies (2-3) As shown below in the figure as an example, if a diverging nozzle section is added to the converging nozzle of the case (B), in order to obtain the same nozzle exit Mach number as case (A), what is the required diverging nozzle exit area? Assume. Total mass flow rate through nozzle, m.mozzle - 780 kg's The outlet of the afterburner is the inlet of the nozzle where velocity - 0 m/s • Flow is isentropic through nozzle Refer the table or equations below if needed
Tailcone Exaustorie Sort section Dil Garatansson Convergent exhaust nozzle Convergent-divergent exhaust duct Ma TABLE A-32 One-dimensional sentropi compressiblollow functions for an ideal gas with = 14 Ma AIA PIP TIT 0 0 00 1.0000 10000 1000 0.1 0.1094 5.8218 0.9930 0.9950 0.9980 0.2 0.2182 2.9635 0.9725 0.9803 0.9921 03 0.3257 2.0351 0.9395 0.9564 0.923 0.4 0.4313 1.5601 0.8956 0.9243 0.9690 0.5 05445 1.3398 0.84.00 0.8852 0.9524 06 0.6348 LIRR2 0.7840 0.8405 0.9328 0.7 0.7318 1.0944 0.7209 0.7916 0.9107 0.8 0.8251 10382 0.6560 0,7400 0.8565 09 0.9146 1.0089 0.5913 0.6870 0.8606 10 LOOXO 1. X 0.5283 0.6319 0.8333 1.2 1.1583 1.0304 0.4124 0.5311 0.7766 1.4 1.2999 11149 0.3142 0.4374 0.7184 1.4254 1.2502 0.2353 0.3557 0.6614 1.8 1.5360 1.4190 0.1740 0.2868 0.6068 2.0 1.6330 1.6875 0.1278 0.2300 0.5556 22 1.7179 2.0050 0.0935 0.1841 0.508 2.4 1.7922 2.4031 0.0684 0.1472 0.4647 2.6 1.8571 2.8960 0.0501 0.1179 0.4252 2.8 1.9140 3.5001 0.0368 0.0946 0.3894 3,0 1.960 42446 0.0272 0.0760 0.3571 5.0 2.2161 25.000 0.0019 0.0113 0.1667 20 2.3495 0 0 MaMa 2+k- M 4 1 1 + Mall 1.6 M P M T 20