Heterogeneous reactions in aircraft gas turbine engines

Details Heterogeneous reactions in aircraft gas turbine engines Heterogeneous reactions in aircraft gas turbine engines

May 2002

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2002georl..29j..66b&link_type=abstract

Geophysical Research Letters, Volume 29, Issue 10, pp. 66-1, CiteID 1424, DOI 10.1029/2000GL011447

Mathematics

Probability

Atmospheric Composition And Structure: Aerosols And Particles (0345, 4801), Atmospheric Composition And Structure: Chemical Kinetic And Photochemical Properties, Atmospheric Composition And Structure: General Or Miscellaneous

Scientific paper

One-dimensional flow models and unity probability heterogeneous rate parameters are used to estimate the maximum effect of heterogeneous reactions on trace species evolution in aircraft gas turbines. The analysis includes reactions on soot particulates and turbine/nozzle material surfaces. Results for a representative advanced subsonic engine indicate the net change in reactant mixing ratios due to heterogeneous reactions is <10-6 for O2, CO2, and H2O, and <10-10 for minor combustion products such as SO2 and NO2. The change in the mixing ratios relative to the initial values is <0.01%. Since these estimates are based on heterogeneous reaction probabilities of unity, the actual changes will be even lower. Thus, heterogeneous chemistry within the engine cannot explain the high conversion of SO2 to SO3 which some wake models require to explain the observed levels of volatile aerosols. Furthermore, turbine heterogeneous processes will not effect exhaust NOx or NOy levels.

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