A simple model for a turbo-prop jet engine is the Air-standard Ideal Brayton cycle, shown in Figure 1. The air in the cycle is defined at each of the states (1-4) and can be treated as an ideal gas throughout. Air enters the Brayton cycle (State 1) at P = 100Pa, T = 300K, and a volumetric flow rate of 5 The pressure ratio across the compressor is 10 and the temperature entering the turbine at 1400K. You may assume that specific heats remain constant at their STP values for all states in the cycle. Determine the following: (a) The thermal efficiency of the cycle (b) The net power developed, in kW General information Critical pressure for air is P = 3.77 106 Pa, and critical temperature is T = 132.4 K Use specific heat ratio of y=1.4 where needed. Use gravitational acceleration of g = 9.8m/s Compressibility chart can be found in the slides, available on Canvas Comp. Heat Exchanger Heat Exchanger S=Constant Qost Turb. Figure 1: Steady-state device representation of an ideal Brayton cycle S=Constant EE Specific volume P=Constant P= Constant cycle Entropy Figure 2: The air-standard ideal Brayton cycle