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Parametric Cycle Analysis of Ideal Turbo Jet Engine

Parametric Cycle Analysis of Ideal Turbo Jet Engine. P M V Subbarao Professor Mechanical Engineering Department Lecture - 8. Selection of Optimal Design Cruising Conditions…. Effect of Flight Mach Number on Compactness. r 0p =5. r 0p =3. r 0p =2. r 0p =1. r 0p =10. r 0p =20.

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Parametric Cycle Analysis of Ideal Turbo Jet Engine

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  1. Parametric Cycle Analysis of Ideal Turbo Jet Engine P M V Subbarao Professor Mechanical Engineering Department Lecture - 8 Selection of Optimal Design Cruising Conditions….

  2. Effect of Flight Mach Number on Compactness r0p=5 r0p=3 r0p=2 r0p=1 r0p=10 r0p=20 r0p=30 t0,cc=4.5 Specific Thrust kN.s/kg Mac

  3. r0p Effect of Flight Mach Number on Fuel Air Ratio t0,cc=4.5 1 2 3 5 10 20 30 Mac

  4. Effect of Flight Mach Number on Fuel Economy r0p=2 r0p=1 r0p=3 r0p=5 r0p=10 r0p=20 r0p=30 t0,cc=4.5 TSFC kg/ kN.hr Mac

  5. r0p Effect of Flight Mach Number on Fuel Air Ratio t0,cc=4.5 1 2 3 5 10 20 30 Mac

  6. Effect of Flight Mach Number on Propulsion Efficiency t0,cc=4.5 r0p= 30 r0p=2 r0p= 5 Mac

  7. r0p Effect of Flight Mach Number on Thermal Efficiency t0,cc=4.5 Mac

  8. Effect of Flight Mach Number on Overall Efficiency t0,cc=4.5 hO r0p Mac

  9. Effect of Pressure Ratio on Compactness Mac=0 Mac=0.5 Mac=1.0 Mac=1.5 Mac=2.0 Mac=2.5 Mac=3.0 t0,cc=4.5 Specific Thrust kN.s/kg rp

  10. Effect of Pressure Ratio on Fuel Economy t0,cc=4.5 Mac TSFC kg/ kN.hr rp

  11. Effect of Pressure Ratio on Fuel Air Ratio t0,cc=4.5 rp

  12. Effect of Pressure Ratio on Propulsive Efficiency t0,cc=4.5 rp

  13. Effect of Pressure Ratio on Thermal Efficiency t0,cc=4.5 rp

  14. Effect of Pressure Ratio on Overall Efficiency t0,cc=4.5 rp

  15. Effect of Pressure Ratio on Compactness Mac=0 Mac=0.5 Mac=1.0 Mac=1.5 Mac=2.0 Mac=2.5 Mac=3.0 t0,cc=4.5 Specific Thrust kN.s/kg rp

  16. inlet 1 2 7 5 6 3 4 Turbo Jet with Afterburner

  17. Elevation of Temperature of the Jet: After Burner : More Energy at Same Life

  18. Minimum Jet Temperature Jet Total Temperature : Jet Static Temperature :

  19. Characterization of AB Jet Maximum obtainable Mach number of Jet

  20. Performance of Jet Propulsive Power or Thrust Power: Specific Thrust S Thrust Specific Fuel Consumption TSFC

  21. W AB W AB W/O AB W/O AB AB & No AB rp = 10 TSFC Specific Thrust

  22. Ideal Afterburning Turbojet Engine Performance : Specific Thrust Vs Compressor Pressure Ratio 2.5 Specific Thrust kN.s/kg 3.0 rp

  23. Ideal Turbojet Engine Performance : Specific Thrust Vs Compressor Pressure Ratio Maircraft Specific Thrust kN.s/kg Compressor Pressure Ratio : rp

  24. Ideal Afterburning Turbojet Engine Performance : TSFC Vs Compressor Pressure Ratio TSFC kg/ kN.hr rp

  25. Effect of Pressure Ratio on Fuel Economy Constant TIT TSFC kg/ kN.hr Mac rp

  26. Ideal Afterburning Turbojet Engine Performance : TSFC Vs Compressor Pressure Ratio rp

  27. Ideal Afterburning Turbojet Engine Performance : Efficiencies Vs Compressor Pressure Ratio rp

  28. Summary of Turbojet Performance • A high compressor pressure ratio is desirable for subsonic flight for good specific thrust and low fuel consumption. • A special care must be used in selecting the compressor pressure ratio for the supersonic flight Mach number. • Rapid drop in specific thrust with pressure ratio at supersonic conditions. • There exist a pressure ratio for each Mach number of a supersonic flight, that gives maximum specific thrust. • The fuel air ratio decreases with increasing Mach number and compressor pressure ratio. • Propulsive efficiency increases with increasing Mach number. Rapid fall in specific thrust under supersonic conditions is a serious concern.

  29. Optimization of Turbojet Performance P M V Subbarao Professor Mechanical Engineering Department Better Deal for Compactness & Fuel Economy…

  30. Optimum Compressor Pressure Ratio • At supersonic flight conditions, a maximum value of Specific thrust is Exhibited at certain compressor pressure ratio. • The value of pressure ratio to maximize the specific thrust at a given flight Mach number should be found by differentiation of specific thrust equation. For Maximum Specific Thrust:

  31. Optimum Compressor Pressure Ratio Vs Mach Number W AB r0p,opt W/o AB Mac

  32. Optimal Turbojet Engine Performance With After Burner Specific Thrust kN.s/kg TSFC kg/ kN.hr Without After Burner Mac

  33. Energy Flow in Jet Engine Energy input Long distance travel demands high flight velocity. High flight velocity leads to drop in compactness and fuel economy. A Single Jet is blackmailing the jet engine !!!

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