A simple gas turbine system is to be modeled using a Brayton cycle. Air enters the compressor at 100 kPa and 300K. The compressor has a pressure ratio of 10 and an isentropic efficiency of 85% (ie. η.-0.85). Due to flow losses in the combustor the air enters the turbine at 950 kPa and 1400 K. The turbine has an exit pressure of i 00 kPa and an isentropic efficiency of 88% (ie, 0.88). Assume constant specific heats. (i. e. Cv 0.717 kJ/kgK, Cp- 1.004 kJ/kgK).

a) Sketch the T-s diagram for the entire system including both the isentropic and actual states
b. for the compressor and turbine. Label the states.
c. Find the actual compressor work (kJ/kg).
d. Find the actual turbine work (kJ/kg) Find the heat transfer into the combustor (kJ/kg)