Parametric Cycle Analysis of Ideal Turbo Jet Engine

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Presentation transcript:

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 t0,cc=4.5 r0p=20 r0p=30 r0p=10 r0p=5 r0p=3 r0p=2 r0p=1 Specific Thrust kN.s/kg Mac

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

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

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

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

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

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

Effect of Pressure Ratio on Compactness 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

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

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

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

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

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

Effect of Pressure Ratio on Compactness 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

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

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

Minimum Jet Temperature Jet Total Temperature : Jet Static Temperature :

Characterization of AB Jet Maximum obtainable Mach number of Jet

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

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

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

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

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

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

Ideal Afterburning Turbojet Engine Performance : TSFC Vs Compressor Pressure Ratio

Ideal Afterburning Turbojet Engine Performance : Efficiencies Vs Compressor Pressure Ratio

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.

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

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:

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

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

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 !!!