Open Access
Table 1
Thermodynamic specifications calculated for the turbojet engine at sea level and speed of 200 m/s.
| Item No. | TurboJet Engine J85GE-21 | T (K) | P (kPa) | ∙ (kg s−1) | Ė ph (kW) | Ė ch (kW) | Ė kn (kW) | Ė t (kW) | |
|---|---|---|---|---|---|---|---|---|---|
| 1 | Diffuser inlet | 298.15 | 101.3 | 28.41 | 0.00 | 0.00 | 568.24 | 568.24 | |
| 2 | Diffuser outlet | 318.05 | 124.24 | 28.41 | 514.563 | 0.00 | 0.00 | 514.56 | |
| 3 | Compressor inlet | 318.05 | 124.24 | 24.15 | 437.378 | 0.00 | 0.00 | 437.37 | |
| 4 | Compressor outlet | 625.68 | 1118.21 | 24.15 | 7,679.526 | 0.00 | 0.00 | 7,679.52 | |
| 5 | Combustion chamber inlet | 625.68 | 1118.21 | 14.49 | 4,607.716 | 0.00 | 0.00 | 4,607.71 | |
| 6 | Turbine inlet | 1709.60 | 2138.78 | 14.89 | 18,409.22 | 0.00 | 0.00 | 18,409.22 | |
| 7 | After burner inlet | 1184.02 | 534.69 | 14.89 | 10,297.360 | 0.00 | 0.00 | 10,297.36 | |
| 8 | After burner outlet | 2933.53 | 1263.82 | 18.55 | 36,170.400 | 0.00 | 0.00 | 36,170.40 | |
| 9 | Exhaust nozzle outlet | 2866.05 | 101.3 | 18.55 | 32,781.32 | 0.00 | 1111.10 | 33,892.43 | |
| 10 | Combustion chamber fuel | 353 | 2757 | 0.4 | 0.00 | 18,282.33 | 0.00 | 18,282.33 | |
| 11 | After burner fuel | 353 | 1103.15 | 1.21 | 0.00 | 55,687.97 | 0.00 | 55,687.98 |
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