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 1 - (1/r) ɣ/ɣ-1 1 - (1/r) ɣ-1/ɣ r ɣ-1 1 - r ɣ-1 1 - (1/r) ɣ/ɣ-1 1 - (1/r) ɣ-1/ɣ r ɣ-1 ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines A turboprop is preferred to turbojet because It has high power for take off It has high propulsive efficiency at high speeds It can fly at supersonic speeds It can fly at high elevations It has high power for take off It has high propulsive efficiency at high speeds It can fly at supersonic speeds It can fly at high elevations ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The net work input required for compressor with increase in clearance volume Increases/decreases depending on compressor capacity Decreases Remains same Increases Increases/decreases depending on compressor capacity Decreases Remains same Increases ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The ratio of the net work obtained from the gas turbine plant to the turbine work is known as Compression ratio Pressure ratio Work ratio None of these Compression ratio Pressure ratio Work ratio None of these ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines In a reciprocating air compressor, the compression work per kg of air Increases as clearance volume decreases Is independent of clearance volume Increases as clearance volume increases Decreases as clearance volume increases Increases as clearance volume decreases Is independent of clearance volume Increases as clearance volume increases Decreases as clearance volume increases ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The blades of gas turbine are made of Carbon steel High nickel alloy High alloy steel Stainless steel Carbon steel High nickel alloy High alloy steel Stainless steel ANSWER DOWNLOAD EXAMIANS APP
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