Question

3.7 A simple twin-spoot turbofan is designed for a business jet. The cruise design point for a Mach number of 0-75 and altitude of 12 500 m (T, " 216.7 K, P.-0-1793 bar, a = 295.1 m/s) is as follows: 9-6 kg/s Airflow Bypass ratio Fan pressure ratio Compressor pressure ratio Turbine inlet temperature Polytropic efficiency (all) 1220K 0.90 Combustion pressure loss Compressor delivery pressure 5% Mechanical efficiencies Combustion efficiency Intake efficiency Nozzle efficiencies 0.99 0-98 0-96 1-00 Separate exhausts are used. Calculate the thrust, fuel flow and SFC [1881 N, 133-6 kg/h, 0-0711 kg/Nh]

Answer 1

G1 Mach nurm ben 0175 altituda Pa - o,93 ban usîng -foimula belou ustng fvimube Mas flow snatz of -fel cala 5FC Stagnation tem inleh

To = 216,1 | l+ o.ax o.5ς25 이 Al6 '구 X 1,1125 то 01 a 241, 08-216 ,チ 24,38 K Po2 x o.l구93 2161ㅋ Temperature often -Er:- ATC fan 02-101 一241.08 285. 3G 2. o 44.23 k far

lou) 1. 1녀 다 0.99 e 181,a K AT ne. înlef lempenauu (1220-234.32- 1,147 X 0.99 TO2 natto О. 31 8 Роз = 285.36x(19) 550.38K em penatou aflen high psuuwu com pousa To 122O 234, 32 Tou Poc

0,236 X0.9 122 0 98 5.7 61803 - 122 0 935.1 Pos Po5 985구、4.4803 494.8 2699 66 oiy24 bar bhot2 A ไธ.calculat beIo ω 285,4 mc , 2324 1. 893 G, 2 87 233.8 o. 3405 x 309.

Fo hot sbeam P6-0.4924 1、852 T6 2 333 h -loox o,2659 o, 287 X G83.9 26, 59 196,28 Οι 1355 Jh4x284 x G 839 011355 2 01135 5 χ 511 - 0.O2896 m

6 Fa 2 C5.5 231.3) +0.02326 Co,265] -0.193)X1o 580'4+o.oo 24 5 х יסו = Fh ニ 830 F-1880. N E 2x o,018 6 x3600 133. 63 kg:h = 33,63 1880 ' .