Compressors, Gas Turbines and Jet Engines For supplying intermittent small quantity of air at high pressure, following compressor is best suited Centrifugal Axial Reciprocating Screw Centrifugal Axial Reciprocating Screw ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines In a single stage, single acting reciprocating air compressor, without clearance volume, the work-done is minimum during None of these Isothermal compression Polytropic compression Isentropic compression None of these Isothermal compression Polytropic compression Isentropic compression ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines In n₁ and n₂ are the indices of compression for the first and second stage of compression, then the ratio of work-done on the first and second stages (W₁/W₂) with perfect intercooling is given by W₁/W₂ = n₂/n₁ W₁/W₂ = n₁/n₂ W₁/W₂ = n₁(n₂ - 1)/n₂(n₁ - 1) W₁/W₂ = n₂(n₁ - 1)/n₁(n₂ - 1) W₁/W₂ = n₂/n₁ W₁/W₂ = n₁/n₂ W₁/W₂ = n₁(n₂ - 1)/n₂(n₁ - 1) W₁/W₂ = n₂(n₁ - 1)/n₁(n₂ - 1) ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The pressure of air at the beginning of the compression stroke is ___ the atmospheric pressure. Less than None of the listed here More than Equal to Less than None of the listed here More than Equal to ANSWER DOWNLOAD EXAMIANS APP
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 The exit velocities of exhaust gases are much higher than those in jet engine All of these 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 The exit velocities of exhaust gases are much higher than those in jet engine All of these The stagnation conditions exist at the combustion chamber ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines High air-fuel ratio is used in gas turbines To increase the efficiency To increase the output To reduce the exit temperature To save fuel To increase the efficiency To increase the output To reduce the exit temperature To save fuel ANSWER DOWNLOAD EXAMIANS APP
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