Colorless distributed combustion (C

Colorless distributed combustion (CDC) has been shown to provide significant improvement in gas turbinecombustor performance. Colorless distributed combustion with swirl is investigated here to developultra-low emissions of NO and CO, and significantly improved pattern factor. Experimental investigationshave been performed using a cylindrical geometry combustor with swirling air injection and axial hot gasexit stream from the combustor. Air was injected tangentially to impart swirl to the flow inside the combustor.The results obtained from the combustor have demonstrated very low levels of NO (3 PPM) andCO (70 PPM) emissions at an equivalence ratio of 0.7 and a high heat release intensity of 36 MW/m3-atm under non-premixed combustion. To further simulate gas turbine operating conditions, inlet airto the combustor was preheated to 600 K temperature and the combustor operated at 2 atm pressure.Results showed very low levels of CO (10 PPM) but the NO increased somewhat to 10 PPM at an equivalenceratio of 0.5 and heat release intensity of 22.5 MW/m3-atm under non-premixed combustion conditions.For premixed combustion, the combustor demonstrated low levels of both NO (5 PPM) and CO(8 PPM) at an equivalence ratio of 0.6 and a heat release intensity of 27 MW/m3-atm. Results are reportedat different equivalence ratios on the emission of NO and CO, lean stability limit and OH chemiluminescence.These results suggest that further performance improvement can be achieved with improved fuelmixture preparation prior to the ignition of fuel at higher operational pressures using swirling combustordesign for our quest to develop ultra low emission high intensity combustor for gas turbine application

Colorless distributed combustion (CDC) has been shown to provide significant improvement in gas turbine
combustor, performance. Colorless distributed combustion with swirl is investigated here to develop
ultra-low emissions of NO and CO and significantly,, Improved pattern factor. Experimental investigations
.Have been performed using a cylindrical geometry combustor with swirling air injection and axial hot gas
exit stream from. The combustor. Air was injected tangentially to impart swirl to the flow inside the combustor.
The results obtained from. The combustor have demonstrated very low levels of NO ( 3 PPM) and
CO ( 70 PPM) emissions at an equivalence ratio of 0.7 and a high heat release intensity of 36 MW / m3
- ATM under non-premixed combustion. To further simulate gas turbine operating. Conditions inlet, air
to the combustor was preheated to 600 K temperature and the combustor operated at 2 atm pressure.
Results. Showed very low levels of CO ( 10 PPM) but the NO increased somewhat to  10 PPM at an equivalence
ratio of 0.5 and heat. Release intensity of 22.5 MW / m3-atm under non-premixed combustion conditions.
For, premixed combustion the combustor demonstrated low levels of. Both NO (5 PPM) and CO
(8 PPM) at an equivalence ratio of 0.6 and a heat release intensity of 27 MW / m3-atm. Results are. Reported
at different equivalence ratios on the emission of NO, and CO lean stability limit and OH  chemiluminescence.
.These results suggest that further performance improvement can be achieved with improved fuel
mixture preparation prior. To the ignition of fuel at higher operational pressures using swirling combustor
design for our quest to develop ultra low. Emission high intensity combustor for gas turbine application.