Compressors, Gas Turbines and Jet Engines In the axial flow gas turbine, the work ratio is the ratio of Output and input Actual total head temperature drop to the isentropic total head drop from total head inlet to static head outlet Actual compressor work and theoretical compressor work Compressor work and turbine work Output and input Actual total head temperature drop to the isentropic total head drop from total head inlet to static head outlet Actual compressor work and theoretical compressor work Compressor work and turbine work ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The indicated work per unit mass of air delivered is Inversely proportional to clearance volume Not affected by clearance volume Directly proportional to clearance volume Greatly affected by clearance volume Inversely proportional to clearance volume Not affected by clearance volume Directly proportional to clearance volume Greatly affected by clearance volume ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines For a two stage compressor, if index of compression for higher stage is greater than index of compression for lower stage, then the optimum pressure as compared to ideal case will Other factors control it Remain unaffected Decrease Increase Other factors control it Remain unaffected Decrease Increase ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Isothermal compression efficiency can be attained by running the compressor At average speed At zero speed At very slow speed At very high speed At average speed At zero speed At very slow speed At very high speed ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Gas turbine cycle with regenerator Allows high compression ratio Increases thermal efficiency Allows operation at very high altitudes Decreases heat loss is exhaust Allows high compression ratio Increases thermal efficiency Allows operation at very high altitudes Decreases heat loss is exhaust ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Maximum temperature in a gas turbine is of the order of 1500°C 1000°C 700°C 2000°C 1500°C 1000°C 700°C 2000°C ANSWER DOWNLOAD EXAMIANS APP
EXAMIANS