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Parametric Study of Turbofan Performance

Parametric Study of Turbofan Performance. P M V Subbarao Professor Mechanical Engineering Department. Identification of Sensitive Design & Operationa Variables ……. Inlet. Performance of An Ideal Turbofan. Performance Analysis of Turbofan. Performance Parameters: Specific Thrust & TSFC

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Parametric Study of Turbofan Performance

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  1. Parametric Study of Turbofan Performance P M V Subbarao Professor Mechanical Engineering Department Identification of Sensitive Design & Operationa Variables ……

  2. Inlet Performance of An Ideal Turbofan

  3. Performance Analysis of Turbofan • Performance Parameters: Specific Thrust & TSFC • 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.

  4. Influence of Fan: Pressure Ratio: Mac = 0.75 r0,p,comp=15.0 a=4.0 T0max=1200K

  5. Combined Effect of Fan & Compressor Pressure Ratios a=4.0 T0max=1200K Mac =0.75

  6. TSFC Combined Effect of Fan & Compressor Pressure Ratios a=4.0 T0max=1200K Mac =0.75

  7. a Optimum Fan Pressure Ratio for Fuel Economy r0,p,comp=24 T0max=1800K Mac =0.9 TSFC =3 =4 =5 =6 7 8 10 12 Fan Pressure Ratio

  8. a Optimum Fan Pressure Ratio for Compactness =3 =4 =5 6 Specific Thrust kN.s/kg 7 8 10 r0,p,comp=24 T0max=1800K Mac =0.9 12 Fan Pressure Ratio

  9. Optimum Fan Pressure Ratio for Propulsion Efficiency r0p,comp=24 T0max=1800K Mac =0.9 a Fan Pressure Ratio

  10. r0p,fan=4.0 Fan Pressure Ratio r0p,fan=4.5 r0p,fan=3.5 r0p,fan=3.0 r0p,fan=2.0 r0p,fan=1.5 Combined Effect of Fan & Compressor Pressure Ratios a=4.0 T0max=1200K Mac =0.75 Specific Thrust kN.s/kg Compressor Pressure Ratio

  11. Combined Effect of Fan & Compressor Pressure Ratios a=4.0 T0max=1200K Mac =0.75 Fan Pressure Ratio TSFC Compressor Pressure Ratio

  12. Fan Effects on Fuel Economy: r0,p,fan=2.5 & Mac=0.75 a =0.5 =1.0 =1.5 =2 TSFC =3 =4 =5 =8 =12 Compressor Pressure Ratio

  13. Optimization Analysis of Turbofan • Operational Parameters : Flight Mach number & Ambient conditions. • Design Variables : Fan Pressure Ratio, Bypass Ratio, Compressor Pressure Ratio, Combustion Chamber Temperature Ratio. • Maximization of specific thrust is not an important issue. • Fuel economy is the main focus for optimization.

  14. Thrust Specific Fuel Consumption TSFC Neglect the value of f in denominator, as the value of f is <<1

  15. Simplified Model for TSFC For maximum fuel economy, maximize the denominator.

  16. Simplified Objective Function Core Effects : Bypass Ratio, Compressor Pressure Ratio & Combustion Chamber Temperature Ratio. Fan Effects : Fan Pressure Ratio & Bypass Ratio.

  17. Selection of Optimum Bypass Ratio As fan handles the entire air intake, Vcoldjet is independent of bypass ratio

  18. Modified Objective Function Rewrite OF for best  as:

  19. Relative change in Turbine TR to BPR

  20. The final Objective function for best 

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