Abstract
A numerical study was performed to determine the effects of operating parameters, including inlet temperature and equivalent ratio on spray combustion characteristics and NOx emission in a gas turbine combustor. A sector model of a typical wall jet can combustor, featured introduction of the primary and dilution air via the wall jet, was used in 3-D calculations. Various operating conditions were applied with inlet temperature from 373 to 1000 K while any others were fixed. The RNG k-ε model and the eddy break-up model have been used for the calculation of turbulence and combustion, respectively. Formation of thermal NOx was determined from the Zeldovich mechanism. It was found that highly heated inlet air makes the flow faster than moderately heated inlet air and the wall jet penetrates deeply up to the centre of combustor for the constant overall equivalent condition, which splits the recirculation region into two parts in the primary zone. The highly heated inlet air shows favourable effects on the temperature distribution, but makes NOx emission increase at the exit of the combustor. The inlet air temperature exerts no large influence on the evaporation rate of liquid fuel in the primary combustion zone, but expedites the evaporation of liquid fuel and reaction at the downstream of the primary combustion zone.
| Original language | English |
|---|---|
| Pages | 197-200 |
| Number of pages | 4 |
| Publication status | Published - 2005 |
| Event | 5th Asia-Pacific Conference on Combustion, ASPACC 2005 - Adelaide, SA, Australia Duration: 2005 Jul 17 → 2005 Jul 20 |
Other
| Other | 5th Asia-Pacific Conference on Combustion, ASPACC 2005 |
|---|---|
| Country/Territory | Australia |
| City | Adelaide, SA |
| Period | 05/7/17 → 05/7/20 |
ASJC Scopus subject areas
- Fluid Flow and Transfer Processes