Combustor re-light procedure

There is provided a method 1100 of operating a gas turbine engine 10. The gas turbine engine 10 comprises a staged combustor 16 having an arrangement of fuel spray nozzles 403, 404 in which fuel flow is biased to a subset of the nozzles 403, 404 adjacent one or more ignitors 405 during a re-light pr...

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Bibliographische Detailangaben
Hauptverfasser:	Craig W Bemment, Christopher P Madden, Benjamin J Keeler, Martin K Yates, Paul W Ferra, Barani P Gunasekaren, Peter Swann, David M Beaven
Format:	Patent
Sprache:	eng
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MECHANICAL ENGINEERING WEAPONS
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Beschreibung
Zusammenfassung:	There is provided a method 1100 of operating a gas turbine engine 10. The gas turbine engine 10 comprises a staged combustor 16 having an arrangement of fuel spray nozzles 403, 404 in which fuel flow is biased to a subset of the nozzles 403, 404 adjacent one or more ignitors 405 during a re-light procedure. The method 1100 comprises transferring heat 1201 from the oil to the fuel before the fuel enters the combustor 16 so as to lower the fuel viscosity to 0.58 mm2 10 /s or lower on entry to the combustor 16 at cruise conditions. Also disclosed is a gas turbine engine 10. Pairs of ignitors may be disposed diametrically opposite each other.