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Optimal Design of a Compact Supersonic Turbojet Engine

Enhance energy and reduce obesity of turbojets with varying Mach numbers. Evaluate compressor pressure ratio for optimal specific thrust. Compare performance with and without afterburner. Design variables for compact turbojet efficiency.

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Optimal Design of a Compact Supersonic Turbojet Engine

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  1. Creation of Compact Supersonic Turbojet P M V Subbarao Associate Professor Mechanical Engineering Department Add More Energy to Lively Jet…

  2. Obesity of Supersonic Turbojet Engines 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

  3. 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 a supersonic flight. • Rapid drop in specific thrust with pressure ratio at supersonic conditions. Rapid fall in specific thrust under supersonic conditions is still a serious concern for domestic use.

  4. inlet 1 2 5 6 3 4 Turbo Jet with Afterburner : Enhanced Energy of Gas

  5. Elevation of Nozzle Inlet Temperature After Burner : More Energy at Same Life

  6. inlet 1 2 7 5 6 3 4 Nozzle with Enhanced Energy of Gas

  7. Jet Static Temperature Jet Total Temperature : Jet Static Temperature :

  8. Enhanced Kinetic energy of AB Jet Maximum obtainable Mach number of Jet

  9. Performance of Turbojet with AB Specific Thrust S Thrust Specific Fuel Consumption TSFC Propulsive Power or Thrust Power:

  10. W AB W AB W/O AB W/O AB Comparative Study of Jet Performance with AB & w/o AB rp = 10 & 0,cAB= 0,cc TSFC Specific Thrust

  11. Ideal Afterburning Turbojet Engine Performance : Specific Thrust Vs Compressor Pressure Ratio AB= cc 2.5 Specific Thrust kN.s/kg 3.0 r0p,comp

  12. Improvement in Specific Thrust AB= cc M=0.0 0.5 There exist a pressure ratio for each Mach number of a supersonic flight, that gives maximum specific thrust. 1.0 1.5 2.0 2.5 Specific Thrust kN.s/kg 3.0 Maircraft M=0.0 0.5 r0p,comp 1.0 1.5 Specific Thrust kN.s/kg 2.0 2.5 3.0 Compressor Pressure Ratio : r0p

  13. Ideal Afterburning Turbojet Engine Performance : TSFC Vs Compressor Pressure Ratio Mac 3.0 TSFC kg/ kN.hr r0p,comp

  14. Penalty on TSFC Mac TSFC kg/ kN.hr TSFC kg/ kN.hr rp rp

  15. Ideal Afterburning Turbojet Engine Performance : f Vs Compressor Pressure Ratio r0p,comp

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

  17. Optimal design of A Turbojet ????

  18. Simple Turbojet :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 for maximum the specific thrust at a given flight Mach number can be evaluated by differentiation of specific thrust equation. For Maximum Specific Thrust:

  19. Design Variables for A Compact Turbojet W AB r0p,opt W/o AB Mac

  20. Performance of the Compact Turbojet Engine With AB Specific Thrust kN.s/kg TSFC kg/ kN.hr W/o AB Mac

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