At the start of cruise the temperature and pressure of the air entering the engine may be taken to be 259 .5K and 46.0 kPa. Assume a pressure ratio of 1.6 for flow through the fan which enters the...

Extracted text: At the start of cruise the temperature and pressure of the air entering the engine may be taken to be 259 .5K and 46.0 kPa. Assume a pressure ratio of 1.6 for flow through the fan which enters the core and a pressure ratio of 25 in the core compressor itself. Assume isentropic efficiencies of 90% in each component. Find the temperature rise across the fan of the flow entering the core compressor, the temperature entering the core compressor and thence the temperature at exit from the core compressor. Fan bypass stator LP Turbine LP Booster stage Bypass jet Fan Core jet Rotor HP Compressor Combustor Core nozzle 2-stage HP turbine Bypass nozzle