Patent ID: 6470684
Filing Date: 2002-10-29
Classification: F23C,F23D,F23R

Abstract:
A gas turbine engine combustion system, comprising:a) a combustion main chamber; b) a combustion pre-chamber upstream and opening into the main chamber, the pre-chamber being of smaller flow area than the main chamber and being disposed about a longitudinal axis; c) a burner face at an upstream end of the pre-chamber; d) a preswirler assembly comprising a plurality of preswirl passages communicating with the upstream end of the pre-chamber for supplying a preswirled air/fuel mixture to the pre-chamber, the preswirl passages being disposed about the longitudinal axis; e) atomizing injection nozzles located in the preswirl passages to inject atomized liquid fuel thereinto, each said injection nozzle including a first electrode means operable to selectively electrostatically charge the first electrode means at a pre-determined polarity thereby to impart electrostatic charge to the atomized fuel; f) second electrode means forming at least portions of the preswirl passages; and g) means operable to selectively electrostatically charge the second electrode means at the same polarity as the first electrode means, thereby to repel the atomized injected fuel from the preswirl passage portions.