1. (20 Points): The combustor discharge into a turbine nozzle has the following parameters: M = 0.48 - T = 1750 K T = 1680 K = Cp 1157 J/kg K y = 1.36 The output flow is currently M2 1.15. What nozzle exit flow angle is needed to make the exit flow choked (M2 1.0)? 2. (10 Points): Our text discusses several hard and soft design constraints for jet engine turbines. Briefly discuss the 5 hard design constraints and what they mean. 3. (10 Points): Briefly discuss the 6 turbine losses associated with turbine engines and ways to help mitigate these losses. 4. (10 Points): Name and define three types of stress on turbine blades. 5. (10 Points): How much work is the turbine section required to draw from the exhaust flow and what is it used for? 6. (10 Points): Why are compressor ratios less than turbine ratios? I.e., why can two turbine stages drive 10 or 20 compressor stages? 7. (10 Points): What is creep in a turbine blade? What are the primary causes and ramifications of turbine blade creep?