Consider an ideal brayton cycle for a jet engine consisting of a compressor, combustion chamber, turbine and nozzle. the pressure and temperature entering the compressor are 105 pa and 300 k respectively. the pressure ratio across the compressor is 6 to 1, the temperature at the turbine inlet is 1000 k, and the pressure at the nozzle exit is 105 pa. assume that cp remains constant through the engine at a value of 1000 j/kgk and  = 1.4. calculate temperature at the exit of the compressor.