Design a turbocharger to boost the inlet air pressure of a single cylinder 1.6 liter, spark engine on an ideal Otto cycle with a compression ratio of 9. Ambient pressure and temperature are 1 bar and 20 *C and the fuel consumption of the engine is 13L/h gasoline at 5600 rom. Exhaust gas-driven turbine is directly connected to air compressor.The isentropic efficiency of the compressor and turbine are 85% and the turbine exhaust pressure can be taken as 2.0 bar. Engine Conpucor Turbine P-Char 1-20 "C (only change fuel flow to fix this) Find a Turbocharger turbine exhaust temperature and turbine work output for the first iteration b. Turbocharger compressor exit temperature and pressure for the first iteration c. Converged turbocharger compressor exit temperature and pressureQ1: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 Power8. Which statement(s) is/are true about a turbine engine (check all that applies): o The turbine engine has a continuous burning process within the casing of the engine. o The ideal air/fuel ratio for combustion within a turbine engine is about 15:1. o ITTs (Internal Turbine temperatures) can reach temperatures of over 4000 "F and relies on additional cooling air is channeled through the engine. o None of the above answers are correct. 9. In your own words, describe, what an inverted oil system is and which type of airplanes benefit from having that type of system