Optimal Design of Turbofan

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Presentation transcript:

Optimal Design of Turbofan P M V Subbarao Professor Mechanical Engineering Department Its Time to think about fuel Economy!!!

Best Selling Turbofans in World CFM series

Current Turbofan Engines Model Thrust Bypass ratio Pressure ratio Applications CFM56-7B18 (86.7 kN) 5.5 32.7 Boeing 737-600 CFM56-7B20 (91.6 kN) 5.4 Boeing 737-600, Boeing 737-700 CFM56-7B22 (101 kN) 5.3 CFM56-7B24 (108 kN) Boeing 737-700, Boeing 737-800, Boeing 737-900 CFM56-7B27 (121 kN) 5.1 Bo

Simplified Objective Function For maximum fuel economy, maximize the denominator. Fan Effects : Fan Pressure Ratio & Bypass Ratio.

Modified Objective Function Rewrite OF for best  as:

Relative change in Turbine TR to BPR

The final Objective function for best 

Optimum Bypass ratio for Minimum TSFC Solve above equation for optimum bypass ratio to give minimum specific fuel consumption. Further use of aopt to calculate velocities of cold and hot jets will give ? ????

Best  for Maximum Fuel Economy : Effect of Compressor Pressure Ratio aopt T04=1700K r0,p,fan=2.0 Mac=0.9 r0,p,comp

Best  for Maximum Fuel Economy : Effect of Fan Pressure Ratio T04=1700K r0,p,comp=24.0 Mac=0.9 aopt r0,p,fan

Best  for Maximum Fuel Economy : Effect of Flight Mach Number T04=1700K r0,p,comp=24.0 r0,p,fan=2.0 aopt r0,p,fan=3.0 Mac

Selection of Optimum Fan Pressure Ratio f is a weak function of  !!!???!!!

Maximum Fuel Economy : Effect of Compressor Pressure Ratio T04=1700K a=4.0 Mac=0.9 rfan,opt rcomp

Maximum Fuel Economy : Effect of Bypass Ratio rfan,opt r0,p,comp=24.0 Mac=0.9 a

Best  for Maximum Fuel Economy : Effect of Fan Pressure Ratio T04=1700K r0,p,comp=24.0 Mac=0.9 aopt r0,p,fan rfan,opt a

Design Charts : Contours of Constant TSFC r0p,fan a

Design Charts : Contours of Constant Specific Thrust r0p,fan a

Latest Turbofan Models form PW PW1100G[47] PW1400G PW1500G[48] PW1900G Fan Diameter 81 in (206 cm) 73 in (185 cm) Bypass ratio 12.5:1 12:1 Static Thrust 110–160 kN 120–140 kN 85–104 kN 76–102 kN Compressor Axial flow, 1 geared fan, 3 stage LPC, 8 stage HPC Combustor Twin annular pre-swirl combustor[49] Turbine Axial flow, 2-stage HP, 3-stage LP Application A320neo family Irkut MC-21 CSeries E-Jets E2 190/195 Service entry January 2016 2018 15 July 2016

Green Engines PW1200G PW1500G PW1100G-JM PW1400G-JM PW1900G Thrust (kN) 67 -- 75 84.5 -104 109 - 156 125 - 138 17 - 23 k Fuel Burn (vs. current engines) -12-16 % -16 % Noise (vs. stage 4) -15 dB -20 dB Emissions - CO2 reduction per a/c (tonnes annually) -2.700 -3.000 -3.600 Emissions - NOx (margin to CAEP 6) -50 % -55 %

How to Facilitates Afterburner ??? Serves, Defense & Space Applications ….

Mixed Flow Turbofan Engine 1 2 6c 3 8 6h 7 4 5 Condition for Ideal Mixing: