Compressors, Gas Turbines and Jet Engines Volumetric efficiency is Reciprocal of compression ratio The ratio of stroke volume to clearance volume The ratio of the air actually delivered to the amount of piston displacement Index of compressor performance Reciprocal of compression ratio The ratio of stroke volume to clearance volume The ratio of the air actually delivered to the amount of piston displacement Index of compressor performance ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines A 3 m³/min compressor means that it Delivers 3 m³/ min of compressed air Compresses 3 m³/min of standard air Compresses 3 m³/ min of free air Delivers 3 m³/ min of compressed air at delivery pressure Delivers 3 m³/ min of compressed air Compresses 3 m³/min of standard air Compresses 3 m³/ min of free air Delivers 3 m³/ min of compressed air at delivery pressure ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The fuel consumption in gas turbines is accounted for by Heating value Higher heating value Higher calorific value Lower heating value Heating value Higher heating value Higher calorific value Lower heating value ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Separators are generally used in air compressor installations Before the inter-cooler Before first stage suction Between the after-cooler and receiver After the inter-cooler Before the inter-cooler Before first stage suction Between the after-cooler and receiver After the inter-cooler ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The volumetric efficiency for reciprocating air compressors is about 70 to 90% 60 to 70% 10 to 40% 40 to 60% 70 to 90% 60 to 70% 10 to 40% 40 to 60% 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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