Modern gas turbine engines operate at fuel-to-air ratios of about 0.02, pressure ratios (ratio of compressor exit pressure to inlet pressure) of nearly 40, and with a turbine inlet temperature (combustor exit temperature) of about 1800 K. At this condition, the gas mixture exiting the combustor comprises about 4% CO2, 4% H2O, 77% N2, and 15% O2 (in mole percentages). Calculate the average properties of the gas exiting the combustor, specifically molecular weight, M, density, , heat capacity, cp (see Appendix II), and sound speed, a. Since we often approximate this gas as heated air, compare these values with corresponding values for air at 1800 K.

Answer rating: 100% (QA)

To calculate the average properties of the gas exiting the combustor we can use the following steps 1 Calculate the molar mass of the gas mixture 2 Ca... View the full answer