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Parametric Study of Turbofan Performance: Sensitivity Analysis of Design and Operational Variables

Explore the influence of key parameters on turbofan performance, including specific thrust, TSFC, flight Mach number, and more. Focus on identifying sensitive design and operational variables to optimize fuel economy and propulsion efficiency. Investigate the combined effects of fan and compressor pressure ratios on performance indicators.

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Parametric Study of Turbofan Performance: Sensitivity Analysis of Design and Operational Variables

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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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