Creation of Compact Supersonic Turbojet

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Presentation transcript:

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 Mac=0 t0,cc=4.5 Mac=0.5 Mac=1.0 Mac=1.5 Mac=2.0 Specific Thrust kN.s/kg Mac=2.5 Mac=3.0 rp

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.

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

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

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

Jet Static Temperature Jet Total Temperature : Jet Static Temperature :

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

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

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

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

Improvement in Specific Thrust Specific Thrust kN.s/kg r0p,comp 2.5 3.0 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 Compressor Pressure Ratio : r0p Specific Thrust kN.s/kg Maircraft M=0.0 0.5 1.0 1.5 2.0 2.5 3.0

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

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

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

Ideal Afterburning Turbojet Engine Performance : Efficiencies Vs Compressor Pressure Ratio

Optimal design of A Turbojet ????

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:

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

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