Compressors, Gas Turbines and Jet Engines More than one stage will be preferred for reciprocating compressor if the delivery pressure is more than 14.7 kg/cm² 6 kg/cm² 2 kg/cm² 10 kg/cm² 14.7 kg/cm² 6 kg/cm² 2 kg/cm² 10 kg/cm² ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines For a two stage reciprocating compressor, compression from p₁ to p₃ is with perfect intercooling and no pressure losses. If compression in both the cylinders follows the same polytropic process and the atmospheric pressure is pa, then the intermediate pressure p₂ is given by p₂ = Pa p₃/p₁ p₂ = p₁. p₃ p₂ = (p₁ + p₃)/2 P₂ = Pa × p₃/p₁ p₂ = Pa p₃/p₁ p₂ = p₁. p₃ p₂ = (p₁ + p₃)/2 P₂ = Pa × p₃/p₁ ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines It is not possible to use closed gas turbine cycle in aeronautical engines because None of these It requires cooling water for its operation It is bulky It is inefficient None of these It requires cooling water for its operation It is bulky It is inefficient ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Pick up the false statement Gas turbine is a self starting unit Exhaust losses in gas turbine are high due to large mass flow rate Overall efficiency of gas turbine plant is lower than that of a reciprocating engine Gas turbine does not require huge quantity of water like steam plant Gas turbine is a self starting unit Exhaust losses in gas turbine are high due to large mass flow rate Overall efficiency of gas turbine plant is lower than that of a reciprocating engine Gas turbine does not require huge quantity of water like steam plant ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The advantage of multistage compression over single stage compression is Lower power consumption per unit of air delivered Higher volumetric efficiency Decreased discharge temperature All of these Lower power consumption per unit of air delivered Higher volumetric efficiency Decreased discharge temperature All of these ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The stagnation pressure rise in a centrifugal compressor takes place In the inlet guide vanes only In the impeller only In the diffuser only In the diffuser and impeller In the inlet guide vanes only In the impeller only In the diffuser only In the diffuser and impeller ANSWER DOWNLOAD EXAMIANS APP
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