Compressors, Gas Turbines and Jet Engines Which of the following statement is correct relating to rocket engines? The combustion chamber in a rocket engine is directly analogous to the reservoir of a supersonic wind tunnel All of these The exit velocities of exhaust gases are much higher than those in jet engine The stagnation conditions exist at the combustion chamber The combustion chamber in a rocket engine is directly analogous to the reservoir of a supersonic wind tunnel All of these The exit velocities of exhaust gases are much higher than those in jet engine The stagnation conditions exist at the combustion chamber ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The inter-cooler pressure, for minimum work required, for a two stage reciprocating air compressor, is given by (where p₁ = Intake pressure of air, p₂ = Inter-cooler pressure, and p₃ = Delivery pressure of air) p₂ = p₁ × p₃ p₂ = p₁ × p₂ p₂ = p₁/p₃ p₂ = p₃/p₁ p₂ = p₁ × p₃ p₂ = p₁ × p₂ p₂ = p₁/p₃ p₂ = p₃/p₁ ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The volumetric efficiency of compressor with increase in compression ratio will Remain same Decrease Increase May increase or decrease depending on clearance volume Remain same Decrease Increase May increase or decrease depending on clearance volume ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Reciprocating air compressor is best suited for Small quantity of air at high pressure Large quantity of air at high pressure Small quantity of air at low pressure Large quantity of air at low pressure Small quantity of air at high pressure Large quantity of air at high pressure Small quantity of air at low pressure Large quantity of air at low pressure ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines A closed cycle gas turbine gives ________ efficiency as compared to an open cycle gas turbine. Same Lower None of these Higher Same Lower None of these Higher ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The maximum temperature in a gas turbine is 500°C 200°C 700°C 1000°C 500°C 200°C 700°C 1000°C ANSWER DOWNLOAD EXAMIANS APP
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