For a two stage reciprocating compressor, compression from p₁ to p₃ is with perfect intercooling and no pressure losses. If compression in both the cylinders follows the same polytropic process and the atmospheric pressure is pa, then the intermediate pressure p₂ is given by

Compressors, Gas Turbines and Jet Engines
For a two stage reciprocating compressor, compression from p₁ to p₃ is with perfect intercooling and no pressure losses. If compression in both the cylinders follows the same polytropic process and the atmospheric pressure is pa, then the intermediate pressure p₂ is given by

p₂ = (p₁ + p₃)/2

p₂ = Pa p₃/p₁

P₂ = Pa × p₃/p₁

p₂ = p₁. p₃

p₂ = (p₁ + p₃)/2

p₂ = Pa p₃/p₁

P₂ = Pa × p₃/p₁

p₂ = p₁. p₃

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Compressors, Gas Turbines and Jet Engines
If infinite number of heaters be used in a gas turbine, then expansion process in turbine approaches

Isochoric

Isothermal

Isentropic

Adiabatic

Isochoric

Isothermal

Isentropic

Adiabatic

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Compressors, Gas Turbines and Jet Engines
The volumetric efficiency of a compressor falls roughly as follows for every 100 m increase in elevation

5%

1.0%

0.1%

0.5%

5%

1.0%

0.1%

0.5%

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Compressors, Gas Turbines and Jet Engines
The following is true for an open cycle gas turbine having exhaust heat exchanger. Atmospheric air before entering the compressor is

Bled gas from turbine is heated and readmitted for complete expansion

Heated

Exhaust gases drive the compressor

Compressed air before entering the combustion chamber is heated

Bled gas from turbine is heated and readmitted for complete expansion

Heated

Exhaust gases drive the compressor

Compressed air before entering the combustion chamber is heated

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Compressors, Gas Turbines and Jet Engines
In axial flow compressor, exit flow angle deviation from the blade angle is a function of

Blade camber

Blade camber and incidence angle

Blade camber and space-chord ratio

Space-chord ratio

Blade camber

Blade camber and incidence angle

Blade camber and space-chord ratio

Space-chord ratio

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Compressors, Gas Turbines and Jet Engines
The pressure ratio in gas turbines is of the order of

0.16736111111111

0.084027777777778

0.37569444444444

2.5423611111111

0.16736111111111

0.084027777777778

0.37569444444444

2.5423611111111

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Compressors, Gas Turbines and Jet Engines

Compressors, Gas Turbines and Jet Engines If infinite number of heaters be used in a gas turbine, then expansion process in turbine approaches

Compressors, Gas Turbines and Jet Engines The volumetric efficiency of a compressor falls roughly as follows for every 100 m increase in elevation

Compressors, Gas Turbines and Jet Engines The following is true for an open cycle gas turbine having exhaust heat exchanger. Atmospheric air before entering the compressor is

Compressors, Gas Turbines and Jet Engines In axial flow compressor, exit flow angle deviation from the blade angle is a function of

Compressors, Gas Turbines and Jet Engines The pressure ratio in gas turbines is of the order of

Compressors, Gas Turbines and Jet Engines
If infinite number of heaters be used in a gas turbine, then expansion process in turbine approaches

Compressors, Gas Turbines and Jet Engines
The volumetric efficiency of a compressor falls roughly as follows for every 100 m increase in elevation

Compressors, Gas Turbines and Jet Engines
The following is true for an open cycle gas turbine having exhaust heat exchanger. Atmospheric air before entering the compressor is

Compressors, Gas Turbines and Jet Engines
In axial flow compressor, exit flow angle deviation from the blade angle is a function of

Compressors, Gas Turbines and Jet Engines
The pressure ratio in gas turbines is of the order of