Intake HP Compressor HPT LPT Turbo-fan 2 **EXAM Cold nozzle 11 Hot nozzle 5h 20 Air info: Cp Air 1000 J/(kg*K) Co gas: 1148 J//kg*K) Rainies=287J/kg Gamma air = 1,4 Gamma gas = 1,33 Fan Combustor A turbo-fan engine has the technical specifications in the table below. Turbo-fan specifications: Calculate: Flight Altitude 3000 Oft a) Fan exit tempink Flight speed M=0.7 b) Fan power in MW Total mass flow 80kg/s BPR=4 c) HPC exit tempink Fan pressure ratio = 1,2 d) HPC power in MW Fan isentropicefficiency 0.9 e) Fuel flow in kg/s HPC pressure ratio = 15 f) HPT exit temperature ink HPC isentropic efficiency 0.8 g) HPT exit pressure in bar Mechanical transmission efficiency both shafts 0.95 Combustor efficiency 0,95 h) LPT exit temperature in K Combustor pressure loss 0,5bar 1) LPT exit pressure in bar Fuel LHV = 43MJ/kg 1) Cold Jetvelocity in m/s Combustor Exit temperature 1500K k) Hot Jet velocity in m/s HPT isentropic efficiency 0.9 1) Netthrustin N (hotjet + coldjet) LPT isentropic efficiency 0.8 m) Propulsive efficiency in % Cold nozzle Isentropic efficiency 0,9 Hot nozzle Isentropicefficiency 0.9 DO NOT NEGLECT FUEL EFFECTS