2. Performance Analysis of A Turboprop Cycle P M V Subbarao Professor Mechanical Engineering Department Looking for Best Opportunities to Realize a True Green Engine ……

3. Turboprop : Just for Fuel Economy 1 2 3 4 5 6 7 p 02 =p 01 = p 03 = p 0∞ T 02 =T 01 = T 03 = T 0∞ p 04 =r 0p,comp p 0∞ = p 05 T 04= =  0p,comp T 0∞ T 05 8

4. Performance of A Turboprop

5. Share of the Propeller : Work Coefficient Turbine Pressure Ratio 0.10 0.167 0.25 0.333 0.5 Compressor Pressure Ratio C prop

6. Share of the Jet : Work Coefficient Turbine Pressure Ratio 0.10 0.167 0.25 0.333 0.5 Compressor Pressure Ratio C jet

7. Total Work Coefficient Turbine Pressure Ratio 0.10 0.167 0.25 0.333 0.5 Compressor Pressure Ratio C turbojet

8. Compactness of A Turboprop Compressor Pressure Ratio Specific Thrust :N.sec/kg Turbine Pressure Ratio 0.10 0.167 0.25 0.33 0.5

9. Fuel Economy of A Turboprop Compressor Pressure Ratio TSFC : mg/N.s Turbine Pressure Ratio 0.10 0.167 0.25 0.33 0.5

10. Efficiency of A Turbo Prop Turbine Pressure Ratio 0.10 0.167 0.25 0.333 0.5 0.10 0.167 0.25 0.333 0.5 Turbine Pressure Ratio Compressor Pressure Ratio pp oo

11. OPTIMIZATION OF THE IDEAL TURBOPROP The question now is: what fraction of the total thrust should be generated by the core in order to produce the maximum work output coefficient. The answer to this question is required in order to properly select the size of the turbine or compressor.

12. Pratt & Whitney PW127G Turboprop The result is class-leading fuel consumption and low green house emissions.

14. Specifications Type: Three spool, free shaft turboprop Inlet: Scroll type Compressor: Twin spool; 1 stage centrifugal LPC, 1 stage centrifugal HPC Burner: Annular, reverse flow Turbine: Three spool, single stage axial HPT, single stage axial LPT, 2 stage power turbine Exhaust: Rear exit, axial flow jet-type outlet

15. Specifications Contd… Power Rating: 3,500 equivalent shaft horsepower at 1,200 rpm Mechanical Horsepower Rating: 3,185 horsepower Thrust Rating: 1750 lbt Rated Torque Output: 13,939 lb/ft Pressure Ratio: 14.5:1 Specific Fuel Consumption:.44 lb/shp/hr

16. Turboprop with Regeneration

17. Philosophy of Fuel Economy

18. Rocket Propulsion P M V Subbarao Professor Mechanical Engineering Department No Breathing of air…… Travel with no Gravity and no Drag….

19. 18 Rocket Thrust Rocket ejects mass at a given momentum rate from the nozzle and receives a thrust in the opposite direction. Momentum rate of ejects: There may also be a thrust component due to pressure field in nozzle. Thrust may be increased by either increasing ejects (propellant) flow rate or exhaust velocity.

20. Flow of Ejects Rocket Motion Pay Load Fuel Nozzle

21. THE TSIOLKOVSKY ROCKET EQUATION