Compressors, Gas Turbines and Jet Engines The overall thermal efficiency of an ideal gas turbine plant is (where r = Pressure ratio) 1 - (1/r) ɣ-1/ɣ 1 - (1/r) ɣ/ɣ-1 1 - r ɣ-1 r ɣ-1 1 - (1/r) ɣ-1/ɣ 1 - (1/r) ɣ/ɣ-1 1 - r ɣ-1 r ɣ-1 ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines If the flow of air through the compressor is perpendicular to its axis, then it is a Turbo compressor Reciprocating compressor Axial flow compressor Centrifugal compressor Turbo compressor Reciprocating compressor Axial flow compressor Centrifugal compressor ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Air-fuel ratio in a jet engine will be of the order of 0.83402777777778 0.41736111111111 0.62569444444444 2.5006944444444 0.83402777777778 0.41736111111111 0.62569444444444 2.5006944444444 ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines In a closed cycle gas turbine, the air is compressed None of these Polytropically Isentropically Isothermally None of these Polytropically Isentropically Isothermally ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The combustion efficiency of a gas turbine using perfect combustion chamber is of the order of 0.85 0.75 0.9 0.99 0.85 0.75 0.9 0.99 ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines A compressor at high altitude will draw Less power Same power More power More/less power depending on other factors Less power Same power More power More/less power depending on other factors ANSWER DOWNLOAD EXAMIANS APP
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