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L22_Real_Turbojet

L22_Real_Turbojet - 3000 M = 0.85 7 T04 = 1500K Pa = 18.75...

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Unformatted text preview: 3000 M = 0.85 7 T04 = 1500K Pa = 18.75 kPa 706A = 2750K Ta = 216.7 K QR = 45000 kJ/kg Po3/P02=25 Afterbuming '2’ Temperature. T/K é 0 0. . 4.00 Entropy. s/R FIGURE 5.17 Ideal turbojet T=s diagram. . P04/P03 = Pa = 18.75 kPa . P06”)05 = 0.95 Ta = K . = y = 1.4 5 T04 .= 1500 K T06A = 2750K QR = Temperature. T/K .00 2.00 4.00 6.00 8.00 Entropy. s/R FIGURE 5.18 Turbojet T—s diagram. TABLE 5.1 Turbojet calculation parameters Adiabatic AVerage specific Component efficiency heat ratio Diffuser m = 0.97 1.40 Compressor 1)c = 0.85 1.37 Burner 17,, = 1.00 1.35 Turbine n, = 0.90 ‘ 1.33 Nozzle 17,, = 0.98 1.36 Fuel heating value, 45,000 kJ/ kg Flight altitude Ambient pressure Ambient temperature (cruise Mach no.) (kPa) (K) Sea level 101.30 288.2 (0) 40,000 ft (12,200 m) 18.75 216.7 (0.85) 60,000 ft (18,300 m) 7.170 p 216.7 - (2.0) 80,000 ft (24,400 m) 2.097 216.7 (3.0) 2.20 2.00 0.04 1 .80 L60 Specific fuel consumption - 0.03 l .40 1.20 1.00 0.02 ‘ 0.80 V 1500 060 Specific thrust 0.01 0.40 0.20 2 3 4 6 8 10 20 30 4O Compressor pressure ratio 60 80 100 FIGURE 5.19 Turbojet static thrust and fuel consumption (M = O). 1 .40 1 .20 0.06 Specific thrust Tm: 1700K I” 1 \\ H \\ / \\ 1600 S 1500 0.05 pecific fuel consumption 0.02 0.20 0.01 2 3 4 6 8 10 20 30 40 60 80 100 Compressor pressure ratio ’ FIGURE 5.20 Turbojet cruise thrust and fuel consumption (M = 0.85). . W‘WNW..... 1.00 0.10 0.80 008 Specific thrust 0.60 0.06 . 1 L"; rha 9 W s 0.40 0.04 kg __ I700 K — kg kN-s Specific fuel 0‘20 consumption 0.02 0 0'002 3 4 6 8 10 20 30 4O 6O 80 100 ' Compressor pressure ratio FIGURE 5.21 Turbojet cruise thrust and fuel consumption (M = 2). 1.00 0.10 0.08 Specific fuel consumption rha 1700 K ? kN-s :600 ' kg kg 500 004 m 0.20 (102 3 4 6 810 20 30 .40 60 80 100 Compressor pressure ratio FIGURE 5.22 Turbojet cruise thrust and fuel consumption (M = 3). ...
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