Kindly provide an example of a design suitable for the above problem statement and answer each bullet point referring to your design.

You have been tasked with the conceptual design a new gas turbine engine to be used on a passenger aircraft. The engine is to be designed for maximum fuel economy at cruise conditions, at which it needs to provide a thrust of 70 kN while the aircraft is flying at a speed of 252 m/s. The atmospheric air temperature and pressure associated with cruise conditions can be taken as -54 C and 0.24 bar. The engine can be in turbojet or turbofan configuration - the choice is left to you (bearing in mind the requirement to maximise fuel economy). State-of-the-art parameters for the engine components that your design may employ are shown in the table below. All other design parameters are for your determination, but must be realistic. Parameter Diffuser polytropic efficiency Fan polytropic efficiency Fan pressure ratio Compressor polytropic efficiency Turbine polytropic efficiency Nozzle polytropic efficiency Combustion chamber pressure drop Turbine inlet temperature Value 98 % 92 % 1.65 91 % 92 % 95 % 5 % 1105 C Present a schematic of the engine, showing the configuration all components and indicating all state points used in calculations. Present full design calculations for the optimal set of engine parameters. All calculations must be performed in an Excel spreadsheet, a copy of which must be submitted with your report. Provide an explanation of the purpose of each calculation step. Present substantial evidence that an optimisation process has been followed to derive final engine parameters. A suitable engine performance metric must drive the optimisation process. List and justify all assumptions made in performing the calculations. Provide an indication of the total mass flow rate of air passing through the engine (in kg/s), and the rate at which fuel will be consumed by the engine (in kg/s). It can be assumed that the engine will burn Jet A-1 aviation fuel. You have been tasked with the conceptual design a new gas turbine engine to be used on a passenger aircraft. The engine is to be designed for maximum fuel economy at cruise conditions, at which it needs to provide a thrust of 70 kN while the aircraft is flying at a speed of 252 m/s. The atmospheric air temperature and pressure associated with cruise conditions can be taken as -54 C and 0.24 bar. The engine can be in turbojet or turbofan configuration - the choice is left to you (bearing in mind the requirement to maximise fuel economy). State-of-the-art parameters for the engine components that your design may employ are shown in the table below. All other design parameters are for your determination, but must be realistic. Parameter Diffuser polytropic efficiency Fan polytropic efficiency Fan pressure ratio Compressor polytropic efficiency Turbine polytropic efficiency Nozzle polytropic efficiency Combustion chamber pressure drop Turbine inlet temperature Value 98 % 92 % 1.65 91 % 92 % 95 % 5 % 1105 C Present a schematic of the engine, showing the configuration all components and indicating all state points used in calculations. Present full design calculations for the optimal set of engine parameters. All calculations must be performed in an Excel spreadsheet, a copy of which must be submitted with your report. Provide an explanation of the purpose of each calculation step. Present substantial evidence that an optimisation process has been followed to derive final engine parameters. A suitable engine performance metric must drive the optimisation process. List and justify all assumptions made in performing the calculations. Provide an indication of the total mass flow rate of air passing through the engine (in kg/s), and the rate at which fuel will be consumed by the engine (in kg/s). It can be assumed that the engine will burn Jet A-1 aviation fuel