Compressors, Gas Turbines and Jet Engines The reason for volumetric efficiency of reciprocating compressor being less than 100 percent is All of these Clearance volume and leakages Pressure drop across the valves Superheating in compressor All of these Clearance volume and leakages Pressure drop across the valves Superheating in compressor ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Ramjet engine Is self operating at zero flight speed Is not self operating at zero flight speed Requires no air for its operation Produces a jet consisting of plasma Is self operating at zero flight speed Is not self operating at zero flight speed Requires no air for its operation Produces a jet consisting of plasma ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The compression ratio in a gas turbine is of the order of 0.20902777777778 0.50069444444444 0.33402777777778 3.5 : 1 0.20902777777778 0.50069444444444 0.33402777777778 3.5 : 1 ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines For slow speed large capacity compressor, following type of valve will be best suited Mechanical valve of the Corliss, sleeve, rotary or semi rotary type Any of the above Disc or feather type Poppet valve Mechanical valve of the Corliss, sleeve, rotary or semi rotary type Any of the above Disc or feather type Poppet valve ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines In a double acting compressor, the air is compressed In a single cylinder on both sides of the piston In two cylinders on both sides of the piston In one cylinder In two cylinders In a single cylinder on both sides of the piston In two cylinders on both sides of the piston In one cylinder In two cylinders ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Which of the following statement is correct relating to rocket engines? 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 The stagnation conditions exist at the combustion chamber ANSWER DOWNLOAD EXAMIANS APP
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