Compressors, Gas Turbines and Jet Engines The maximum temperature in a gas turbine is 1000°C 700°C 200°C 500°C 1000°C 700°C 200°C 500°C ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Losses in a centrifugal compressor are due to Inlet losses Impeller channel losses Diffuser losses All of the listed here Inlet losses Impeller channel losses Diffuser losses All of the listed here ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The effective power of gas turbines is increased by adding the following in compressor Hydrogen Nitrogen Carbon dioxide Ammonia and water vapour Hydrogen Nitrogen Carbon dioxide Ammonia and water vapour ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The temperature of air at the beginning of the compression stroke is ________ the atmospheric temperature. Less than Equal to More than None of these Less than Equal to More than None of these ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The overall thermal efficiency of an ideal gas turbine plant is (where r = Pressure ratio) 1 - r ɣ-1 r ɣ-1 1 - (1/r) ɣ-1/ɣ 1 - (1/r) ɣ/ɣ-1 1 - r ɣ-1 r ɣ-1 1 - (1/r) ɣ-1/ɣ 1 - (1/r) ɣ/ɣ-1 ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Which one of the following is the effect of blade shape on performance of a centrifugal compressor? Backward curved blades has poor efficiency Backward curved blades lead to stable performance Forward curved blades has higher efficiency Forward curved blades produce lower pressure ratio Backward curved blades has poor efficiency Backward curved blades lead to stable performance Forward curved blades has higher efficiency Forward curved blades produce lower pressure ratio ANSWER DOWNLOAD EXAMIANS APP
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