Compressors, Gas Turbines and Jet Engines A compressor at high altitudes will require ___ power. More Less None of the listed here Same More Less None of the listed here Same ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The power available for takeoff and climb in case of turbojet engine as compared to reciprocating engine is Less More Same May be less or more depending on ambient conditions Less More Same May be less or more depending on ambient conditions ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Isothermal compression though most efficient, but is not practicable because It does not increase pressure much It is impossible in practice Compressor has to run at very slow speed to achieve it It requires very big cylinder It does not increase pressure much It is impossible in practice Compressor has to run at very slow speed to achieve it It requires very big cylinder ANSWER DOWNLOAD EXAMIANS APP
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 Heated Exhaust gases drive the compressor Bled gas from turbine is heated and readmitted for complete expansion Compressed air before entering the combustion chamber is heated Heated Exhaust gases drive the compressor Bled gas from turbine is heated and readmitted for complete expansion Compressed air before entering the combustion chamber is heated ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The overall isothermal efficiency of compressor is defined as the ratio of Isothermal h.p. to adiabatic h.p. Power to drive compressor to isothermal h.p. Isothermal h.p. to the BHP of motor Work to compress air isothermally to work for actual compression Isothermal h.p. to adiabatic h.p. Power to drive compressor to isothermal h.p. Isothermal h.p. to the BHP of motor Work to compress air isothermally to work for actual compression ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The thermal efficiency of a simple gas turbine for a given turbine inlet temperature with increase in pressure ratio Decreases First increases and then decreases First decreases and then increases Increases Decreases First increases and then decreases First decreases and then increases Increases ANSWER DOWNLOAD EXAMIANS APP
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