Ambient conditions: Turbine inlet temperature: Reservoir temperature: Dead state conditions: Compressor polytropic efficiency: Turbine polytropic efficiency: Combustion efficiency: Mechanical efficiency: Combustor pressure drop: Regenerator air pressure drop: Ta=293 K, Pa = 100 kPa 1355 K 1555 K same as ambient noo,e = 0.86 noo,t = 0.84 = 0.98 = nm 0.99 App = 0.02 P02 Apha = 0.03 Po2 Regenerator exhaust gas pressure drop: Aphg Regenerator effectiveness: = 0.70 0.04 Pa In this project, you will perform an exergy analysis on a gas turbine power plant that employs regeneration. In the simplified analysis that we initially undertook in class, the efficiency curves seemed to indicate that low compressor pressure ratios were ideal. If we analyze such a cycle with real components, however, we find that there is an optimal pressure ratio that yields the best second-law efficiency. This optimal pressure ratio depends on the turbine inlet temperature and other parameters. Your task in the project is to map the variation of the various performance metrics as a function of compressor pressure ratio. Based on these data, you will select an appropriate pressure ratio for your design. In the analysis, use constant specific heats with the same cp and y value throughout the engine: 1.005 kJ/(kg K) y = 1.400 Your results should include: 1. A quantitative T-s diagram for the design pressure ratio, generated in plotting software and showing the state points with isobars for all of the relevant pressures. 2. A plot of the fuel-to-air ratio f as a function of the compressor pressure ratio, generated using Figure 2.17. Where the heat transfer value is required for the combustor, employ the heating value associated with Figure 2.17 (see the Gas Turbine Theory text). 3. A plot of the specific fuel consumption as a function of compressor pressure ratio (use units of kg/(kWh)).