Compressors, Gas Turbines and Jet Engines The combustion efficiency of a gas turbine using perfect combustion chamber is of the order of 0.75 0.85 0.9 0.99 0.75 0.85 0.9 0.99 ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines If infinite number of heaters be used in a gas turbine, then expansion process in turbine approaches Isochoric Adiabatic Isothermal Isentropic Isochoric Adiabatic Isothermal Isentropic ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The efficiency of a jet engine is higher at High altitudes Low speeds Low altitudes High speeds High altitudes Low speeds Low altitudes High speeds ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The specific output per kg mass flow rate of a gas turbine (having fixed efficiencies of compressor and turbine and fixed higher and lower temperature) with increase in pressure ratio will Increase first at slow rate and then fast Decrease continuously Increase first at fast rate and then slow First increase, reach maximum and then decrease Increase first at slow rate and then fast Decrease continuously Increase first at fast rate and then slow First increase, reach maximum and then decrease ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Turbofan engine employs No air stream Two or more air streams One air stream Solid fuel firing No air stream Two or more air streams One air stream Solid fuel firing ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Which of the following statement is correct relating to rocket engines? The stagnation conditions exist at the combustion chamber The exit velocities of exhaust gases are much higher than those in jet engine All of these The combustion chamber in a rocket engine is directly analogous to the reservoir of a supersonic wind tunnel The stagnation conditions exist at the combustion chamber The exit velocities of exhaust gases are much higher than those in jet engine All of these The combustion chamber in a rocket engine is directly analogous to the reservoir of a supersonic wind tunnel ANSWER DOWNLOAD EXAMIANS APP
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