Performance Analysis of A Turboprop Cycle

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Performance Analysis of A Turboprop Cycle

• P M V Subbarao
• Professor
• Mechanical Engineering Department

Looking for Best Opportunities to Realize a True
Green Engine
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Turboprop Just for Fuel Economy
T05
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p02p01 p03 p08 T02T01 T03 T08
p04 r0p,comp p08 p05 T04 t0p,comp T08
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Performance of A Turboprop
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Share of the Propeller Work Coefficient
Turbine Pressure Ratio
0.10
0.167
Cprop
0.25
0.333
0.5
Compressor Pressure Ratio
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Share of the Jet Work Coefficient
Turbine Pressure Ratio
0.5
0.333
0.25
Cjet
0.167
0.10
Compressor Pressure Ratio
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Total Work Coefficient
Turbine Pressure Ratio
0.10
0.167
0.25
0.333
Cturbojet
0.5
Compressor Pressure Ratio
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Compactness of A Turboprop
Turbine Pressure Ratio
0.10
0.167
Specific Thrust N.sec/kg
0.25
0.33
0.5
Compressor Pressure Ratio
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Fuel Economy of A Turboprop
Turbine Pressure Ratio
0.5
0.33
TSFC mg/N.s
0.25
0.167
0.10
Compressor Pressure Ratio
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Efficiency of A Turbo Prop
Turbine Pressure Ratio
0.10
0.167
hp
0.25
Turbine Pressure Ratio
0.333
0.10
0.5
0.167
0.25
ho
0.333
0.5
Compressor Pressure Ratio
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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.
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Pratt Whitney PW127G Turboprop
The result is class-leading fuel consumption and
low green house emissions.
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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

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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 14.51
• Specific Fuel Consumption .44 lb/shp/hr

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Turboprop with Regeneration
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Philosophy of Fuel Economy
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Rocket Propulsion

• P M V Subbarao
• Professor
• Mechanical Engineering Department

No Breathing of air Travel with no Gravity and
no Drag.
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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.

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Pay Load
Fuel
Rocket Motion
Nozzle
Flow of Ejects
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THE TSIOLKOVSKY ROCKET EQUATION