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Aviation and the Global Atmosphere

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<strong>Aviation</strong> <strong>and</strong> <strong>the</strong> <strong>Global</strong> <strong>Atmosphere</strong><br />

Secondary products (e.g., NO, NO 2 , N 2 O, SO 2 , CO, stable HC) NO x is little changed by flow through turbine. Oxidation of NO <strong>and</strong> NO 2 to HONO<br />

Oxidation products of secondary combustion species (e.g.,<br />

HNO 2 , HNO 3 , SO 3 , H 2 SO 4 , H 2 O 2 , HNO)<br />

<strong>and</strong> HNO 3 , occurring mainly in <strong>the</strong> high-pressure turbine, is a few percent or less.<br />

For civil engines, CO <strong>and</strong> HC are relatively unchanged in <strong>the</strong> turbine, but<br />

significant reductions can occur <strong>the</strong>re in advanced military engines. Accurate NOx predictions <strong>and</strong> measurements are now routinely performed for assessment<br />

purposes.<br />

Chemical mechanisms <strong>and</strong> reaction rates of trace species are not well known<br />

over <strong>the</strong> range of post-combustor conditions. The impact of fluid mechanics on<br />

chemical evolution is not yet fully evaluated by models or measurements.<br />

Reactive species (e.g., O, OH, HO 2 , SO, H 2 , H, N, CH) As above, but validation of trace species chemistry mechanisms, via<br />

measurements, is also needed over <strong>the</strong> relevant temperature <strong>and</strong> pressure range<br />

for both classes. Fur<strong>the</strong>r modeling is required to make <strong>the</strong> connection with<br />

species for which measurements are not available.<br />

7.6.4.1. Primary Exhaust Constituents (H 2O, CO 2, N 2O 2)<br />

Apart from <strong>the</strong> small effect of reactions involving trace species, changes in major species concentration in <strong>the</strong> turbine <strong>and</strong> nozzle flow path are caused by <strong>the</strong> diluting<br />

effect of cooling air. CO 2 changes less than a few tenths of a percent as a result of oxidation of CO (increases in H 2 O from HO x recombination are even smaller). This<br />

CO 2 fractional increase may grow in <strong>the</strong> first stages of <strong>the</strong> high-pressure turbine as more advanced cycles are implemented because associated cycle changes may<br />

result in relatively more CO at <strong>the</strong> entrance to <strong>the</strong> turbine (Godin et al., 1995, 1997; Leide <strong>and</strong> Stouffs, 1996). Current small changes <strong>and</strong> likely future changes in<br />

primary exhaust constituents can be predicted with sufficient accuracy (Dryer et al., 1993) for assessment needs, however, <strong>and</strong> <strong>the</strong> levels are all relatively easy to<br />

derive from measurements.<br />

http://www.ipcc.ch/ipccreports/sres/aviation/105.htm (2 von 4)08.05.2008 02:43:40

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