Patent ID: 6684640
Filing Date: 2004-02-03
Classification: F23D,F23R

Abstract:
A gas turbine engine combustion system, comprising: a radial inflow swirler for mixing gaseous fuel and air, a combustion pre-chamber and a combustion main chamber, the swirler, the pre-chamber and the main chamber having a common longitudinal axis and being arranged in a flow sequence, the swirler comprising air and gas fuel passages angularly arrayed around the pre-chamber, the passages being oriented tangentially to a notional circle centered on the common longitudinal axis, thereby in operation to impart a common swirling motion to streams of fuel and air as they enter the pre-chamber from the passages, each gas fuel passage having an exit situated immediately downstream of an exit of an air supply passage with respect to a direction of swirl and being sized relative to the air supply passage such that at least at a predetermined power condition of the gas turbine engine, a mass mean velocity of the fuel and air streams at said notional circle are closely matched to each other.