Problem #2; Steam Flow to Main Engine Public domain information for the single main steam turbine engine inlet and a reasonable assumption of the exit conditions are: Inlet Tin = 355.C; Pin = 3500kPa Exit Pout = 25kPa; x = 0.95 What is the mass flow to the main engine to achieve the maximum engine power (20 points) You may disregard the velocity terms and potential energy change in the energy equation Assume that the turbine is adiabaticQ1:The following are the design parameters of a simple cycle single shaft gas turbine engine. T1 = 288 K, P1 = 101 kPa. Compressor pressure ratio: 18 TET 1500 K Compressor and turbine efficiency: 0.88 LHV 43 MJ/kg Combustor pressure loss (% of CDP) 5 Mass Flow 120 kg/s Include the fuel flow in your mass flow calculations. Calculate the power output and thermal efficiency of the gas turbine engine. Cold (compressor) Cp and y: 1000 J/kg/K and 1.4 respectively Hot (combustor, turbine) Cp and y: 1150 J/kg/K and 1.3 respectively. Fuel CC Compressor Turbine G Power to Compressor Net PowerA turbojet engine has a turbine that receives combustion gases at 1200 K and 15 bar from the engine combustion chamber. These gases are then fed from the turbine exit to a nozzle, which exhausts to the atmosphere at 0.9 bar. If the combustion gases can be considered air, which is an ideal gas mixture, and both turbine and nozzle are isentropic, what are the temperatures at the turbine and nozzle exits, and the velocity at the nozzle exit? The gases at the turbine exit are at 3 bar and have negligible velocity. Draw a labeled process flow diagram of this process as part of your solution