Compressors, Gas Turbines and Jet Engines The hottest point in a gas turbine is at the tip between ~ to i of the blade height in the center at the base at the tip between ~ to i of the blade height in the center at the base ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The criterion of the thermodynamic efficiency for rotary compressor is Isentropic compression Polytropic compression None of the listed here Isothermal compression Isentropic compression Polytropic compression None of the listed here Isothermal compression ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines There is a certain pressure ratio (optimum) for a gas turbine at which its thermal efficiency is maximum. With increase in turbine temperature, the value of pressure ratio for the peak efficiency would Decrease Increase None of these Remain same Decrease Increase None of these Remain same ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Which of the following plants is smallest and lightest for generating a given amount of power? Gas turbine plant Solar plant Petrol engine Diesel engine Gas turbine plant Solar plant Petrol engine Diesel engine ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Which of the following fuels can be used in turbojet engines? Liquid hydrogen High speed diesel oil Methyl alcohol Kerosene Liquid hydrogen High speed diesel oil Methyl alcohol Kerosene 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 = n₁(n₂ - 1)/n₂(n₁ - 1) W₁/W₂ = n₂/n₁ W₁/W₂ = n₂(n₁ - 1)/n₁(n₂ - 1) W₁/W₂ = n₁/n₂ W₁/W₂ = n₁(n₂ - 1)/n₂(n₁ - 1) W₁/W₂ = n₂/n₁ W₁/W₂ = n₂(n₁ - 1)/n₁(n₂ - 1) W₁/W₂ = n₁/n₂ ANSWER DOWNLOAD EXAMIANS APP
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