Compressors, Gas Turbines and Jet Engines The ratio of work done per cycle to the swept volume in case of compressor is called Mean effective pressure Compressor efficiency Compression index Compression ratio Mean effective pressure Compressor efficiency Compression index Compression ratio ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The overall isothermal efficiency of compressor is defined as the ratio of Work to compress air isothermally to work for actual compression Isothermal h.p. to the BHP of motor Power to drive compressor to isothermal h.p. Isothermal h.p. to adiabatic h.p. Work to compress air isothermally to work for actual compression Isothermal h.p. to the BHP of motor Power to drive compressor to isothermal h.p. Isothermal h.p. to adiabatic h.p. ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Gas turbine cycle with regenerator Allows high compression ratio Allows operation at very high altitudes Decreases heat loss is exhaust Increases thermal efficiency Allows high compression ratio Allows operation at very high altitudes Decreases heat loss is exhaust Increases thermal efficiency ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines In a turbo jet engine, subsequent to heat addition to compressed air, to get the power output, the working substance is expanded in Turbine blades, which is essentially an isentropic process Turbine blades, which is a constant volume process Exit nozzle, which is essentially an isentropic process Exit nozzle, which is a constant volume process Turbine blades, which is essentially an isentropic process Turbine blades, which is a constant volume process Exit nozzle, which is essentially an isentropic process Exit nozzle, which is a constant volume process ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The maximum propulsion efficiency of a turbojet is attained at around following speed 1050 km/hr 1700 km/hr 550 km/hr 2400 km/hr 1050 km/hr 1700 km/hr 550 km/hr 2400 km/hr ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The thermal efficiency of a simple gas turbine for a given turbine inlet temperature with increase in pressure ratio First increases and then decreases Increases Decreases First decreases and then increases First increases and then decreases Increases Decreases First decreases and then increases ANSWER DOWNLOAD EXAMIANS APP
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