Analysis of Turbofan Engine

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Presentation transcript:

Analysis of Turbofan Engine P M V Subbarao Professor Mechanical Engineering Department How to decide Cold Vs Hot ???

Ideal Turbofan Cycle Inlet 2 3 7c 7h 4 1 5 6 Total thrust is generated by both cold and hot jets..

Analysis of fan Analysis of Fan 2 3 Inlet 2 3 Analysis of fan Design Parameter : Stagnation pressure ratio

Analysis of Compressor Inlet 4 3 Design Parameter : Stagnation pressure ratio

5 Inlet 4

Combined Gas Dynamic & Thermodynamic SSSF model for Turbine 6 5 Inlet

Vigor of Hot Jet

Combined Gas Dynamic & Thermodynamic SSSF model for Hot Nozzle

Available life at the inlet to the nozzle will decide the magnitude of T7h.

Combined Gas Dynamic & Thermodynamic SSSF model for Cold Nozzle

Generation of Thrust : The Capacity Propulsive Power or Thrust Power: Specific Thrust based on core flow S Specific Thrust based on total flow S

Thrust Ratio Ratio of specific thrust of core stream to specific thrust of fan stream.

Thrust Specific Fuel Consumption TSFC

Aviation Appreciation Propulsion Efficiency

Performance Analysis of Turbofan Operational Parameters : Flight Mach number & Ambient conditions. Design Variables : Fan Pressure Ratio, Bypass Ratio, Compressor Pressure Ratio, Combustion Chamber Temperature Ratio. Fan Effects : Fan Pressure Ratio Bypass Ratio. Fan Stream Thrust Vs Total Thrust.

Utility of of Fan Bypass Ratio TSFC r0,p,fan=2.5 r0,p,comp=15 T0max=1200K Mac =0.75

Fan Effects …. : Fan Pressure Ratio: Mac = 0.75 r0,p,comp=15.0 a=4.0 T0max=1200K

Effect of Flight Mach Number : Compactness Specific Thrust kN.s/kg Mach Number

Effect of Flight Mach Number : Fuel Economy TSFC Mach Number

Effect of Flight Mach Number : Propulsion Efficiency