1. Modern aircraft gas turbine engines have pressure ratios of 30 or higher. Take that value with compressor inlet conditions of 1 bar and 300 K and a turbine inlet temperature of 1700 K and calculate the cycle efficiency. Then calculate the back work ratio. Assume the compressor and turbine are ideal. What is the entropy generation for the compressor and for the turbine?
2. Compressor technology has progressed further than turbine technology so compressor isentropic efficiencies approach 98% while those for turbines are nearer 92%.