Air flows through a cylindrical combustion chamber of diameter 0.3 m and length 3 m as shown in the figure below. M₁ T₁ P₁ 2 M₂ T₂ P₂ Stations (1) and (2) are the inlet and outlet, respectively. The inlet stagnation temperature is 1,000 K and the inlet stagnation pressure is 1.5 MPa. a) If the skin friction coefficient is Cf = 0.004 (approximately uniform) and no combustion takes place, what will be the inlet Mach number if it is subsonic and the exit Mach number is unity? What are the values of static and stagnation pressure at the exit? b) If combustion takes place and the heat of reaction is 600 kJ/kg of mixture, neglecting frictional effects, and if the inlet Mach number is 0.25, what is the exit Mach number? What are the values of static and stagnation pressure at the exit? The combustion process may be simulated by simple heating with constant specific heat ratio. The fluid may be considered a perfect gas with y = 1.4 and a molecular weight of 29 kg/kmol.

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... Moving to another question will save this response. Question 7 Compressed air with a flowrate of 8 kg/min flows through a two-stage turbine and heat exchanger system as follows: • At the entrance to the system (point 1), the pressure of the air is 8 bar and the temperature of the air is 359 K. • From 1-2 the air passes through a heat exchanger which increases its temperature to 922 K. • From 2-3 the air passes through a turbine, with a pressure ratio of 3 (i.e. P₂/p₂=3). This first turbine has an isentropic efficiency of 65%. • From 3-4 the air passes through a second heat exchanger, which increases its temperature back up to 922 K. • From 4-5 the air passes through a second turbine with a pressure ratio of 3 and an isentropic efficiency of 80%. The properties of air are: cp = 1.005 kJ/kgk, cv = 0.718 kJ/kgK, R = 0.287 kJ/kgK, and y= 1.4. Select the correct value for each of the following values: ₂) a. The heat transfer to the air in the first heat exchanger (i.e. ₁) i in kW: b.…

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