Compressors, Gas Turbines and Jet Engines Propulsive efficiency is defined as ratio of Engine output and propulsive power Thrust power and propulsive power Propulsive power and fuel input Thrust power and fuel energy Engine output and propulsive power Thrust power and propulsive power Propulsive power and fuel input Thrust power and fuel energy ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines For an irreversible gas turbine cycle, the efficiency and work ratio both depend on Pressure ratio alone Minimum cycle temperature alone Both pressure ratio and maximum cycle temperature Maximum cycle temperature alone Pressure ratio alone Minimum cycle temperature alone Both pressure ratio and maximum cycle temperature Maximum cycle temperature alone ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The maximum temperature in a gas turbine is 700°C 1000°C 200°C 500°C 700°C 1000°C 200°C 500°C ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The pressure ratio of an ideal vaned compressor with increase in mass flow rate Decreases Increases Remain constant First decreases and then increases Decreases Increases Remain constant First decreases and then increases ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines To avoid moisture troubles, the branch connections from compressed air lines should be taken from Top side of main Bottom side of main Right side of main Left side of main Top side of main Bottom side of main Right side of main Left side of main ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The work ratio of a gas turbine plant is defined as the ratio of Net work output and heat supplied Actual heat drop and isentropic heat drop Net work output and isentropic heat drop Net work output and work done by turbine Net work output and heat supplied Actual heat drop and isentropic heat drop Net work output and isentropic heat drop Net work output and work done by turbine ANSWER DOWNLOAD EXAMIANS APP
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