In a gas turbine jet engine, the pressure of the incoming air is increased’ by flowing through a compressor; the air then enters a combustor that looks vaguely like a long can (sometimes called the combustion can). Fuel is injected in, to the combustor and burns with the air, and then the burned fuel-air mixture exits the combustor at a higher temperature than the air coming into the combustor. (Gas turbine jet engines are discussed in Ch. 9.) The pressure of the flow through the combustor remains relatively constant; that is, the combustion process is at constant pressure. Consider the case where the gas pressure and temperature entering the combustor are 4 × 106 N/m2 and 900 K, respectively, and the gas temperature exiting the combustor is 1500 K. Calculate the gas density at (a) the inlet to the combustor and (b) the exit of the combustor. Assume that the specific gas constant for the fuel-air mixture is the same as that for pure air.
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