Modern gas turbine engines operate at fuel-to-air ratios of about 0.02, pressure ratios (ratio of compressor exit
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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.
Related Book For
Thermodynamics An Engineering Approach
ISBN: 978-0073398174
8th edition
Authors: Yunus A. Cengel, Michael A. Boles
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