You work for a gas turbine design company and have a client who has a fairly loose specification for a gas turbine engine. You are required to design an aviation gas turbine to power the aircraft with minimum thrust requirement of 110,000 N from one engine. Though the client wants to achieve lowest fuel consumption possible. The following guideline efficiencies have been given to assist in the design process. Fan, compressor and turbine polytropic efficiencies Propelling nozzles isentropic efficiencies Mechanical transmission of each spool Combustion efficiency 90% 94% 96% 99% You have total discretion to assume the temperatures, pressures and any other variable you deem necessary unless stated above, though assumptions need to be of sensible values that are justified given current engineering technology. Your brief summary report should include as a minimum the following; 1- Discuss selection of different components and types. You need to demonstrate why a particular type/component or value has been selected as compared to others. Your answers could have both numerical and theoretical response to this part. 2- Specific Fuel Consumption 3- Thrust calculations of all nozzles.