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Creation of Compact Supersonic Turbojet

Creation of Compact Supersonic Turbojet. P M V Subbarao Associate Professor Mechanical Engineering Department. Add More Energy to Lively Jet…. Obesity of Supersonic Turbojet Engines. M ac =0. M ac =0.5. M ac =1.0. M ac =1.5. M ac =2.0. M ac =2.5. M ac =3.0. t 0,cc =4.5.

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Creation of Compact Supersonic Turbojet

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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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