Compressors, Gas Turbines and Jet Engines The degree of reaction in an axial flow compressor is defined as the ratio of static enthalpy rise in the Rotor to static enthalpy rise in the stator Stator to static enthalpy rise in the stage Rotor to static enthalpy rise in the stage Stator to static enthalpy rise in the rotor Rotor to static enthalpy rise in the stator Stator to static enthalpy rise in the stage Rotor to static enthalpy rise in the stage Stator to static enthalpy rise in the rotor ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Intercooling in gas turbines Increases net output but decreases thermal efficiency Increases net output and thermal efficiency both Decreases net output but increases thermal efficiency Decreases net output and thermal efficiency both Increases net output but decreases thermal efficiency Increases net output and thermal efficiency both Decreases net output but increases thermal efficiency Decreases net output and thermal efficiency both ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Volumetric efficiency of air compressors is of the order of 40 - 50% 60 - 70% 20 - 30% 70 - 90% 40 - 50% 60 - 70% 20 - 30% 70 - 90% 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 = n₂(n₁ - 1)/n₁(n₂ - 1) W₁/W₂ = n₁(n₂ - 1)/n₂(n₁ - 1) W₁/W₂ = n₂/n₁ W₁/W₂ = n₁/n₂ W₁/W₂ = n₂(n₁ - 1)/n₁(n₂ - 1) W₁/W₂ = n₁(n₂ - 1)/n₂(n₁ - 1) ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines A simple turbojet engine is basically A propeller system Ramjet engine Gas turbine engine equipped with a propulsive nozzle and diffuse Chemical rocket engine A propeller system Ramjet engine Gas turbine engine equipped with a propulsive nozzle and diffuse Chemical rocket engine ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The air-fuel ratio in gas turbines is of the order of 30: 1 50: 1. 15: 1 7: 1 30: 1 50: 1. 15: 1 7: 1 ANSWER DOWNLOAD EXAMIANS APP
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