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Heterogeneous reactions in aircraft gas turbine engines
Author(s) -
Brown R. C.,
MiakeLye R. C.,
Lukachko S. P.,
Waitz I. A.
Publication year - 2002
Publication title -
geophysical research letters
Language(s) - English
Resource type - Journals
SCImago Journal Rank - 2.007
H-Index - 273
eISSN - 1944-8007
pISSN - 0094-8276
DOI - 10.1029/2000gl011447
Subject(s) - combustion , nozzle , soot , mixing (physics) , gas turbines , environmental science , turbine , wake , trace gas , jet engine , mechanics , particulates , exhaust gas , thermodynamics , atmospheric sciences , meteorology , chemistry , physics , mechanical engineering , engineering , organic chemistry , quantum mechanics
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 O 2 , CO 2 , and H 2 O, and <10 −10 for minor combustion products such as SO 2 and NO 2 . 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 SO 2 to SO 3 which some wake models require to explain the observed levels of volatile aerosols. Furthermore, turbine heterogeneous processes will not effect exhaust NO x or NO y levels.