| 摘要 |
A burner for a gas-turbine engine comprises a swirler and a combustion chamber. The swirler comprises a number of vanes arranged in a circle, each adjacent pair of vanes defining a flow slot for the flow of air and fuel into the swirler, the air and fuel being mixed and supplied in swirling form to the combustion chamber. The swirler also has, in a preferred embodiment, a partitioning device, which divides the flow of air along each flow slot into first and second air flows, and has in one side of the partitioning device at least one fuel-supply port for supplying fuel to one of the first and second air flows. When the burner is in use, the relevant air flow causes fuel supplied to the at least one fuel-supply port to form a film of fuel over the relevant side of the partitioning device. The film is arranged to leave the relevant side of the partitioning device substantially in a region of high shear between adjacent flows in the burner. These adjacent flows are: a) the annular swirling fuel-air mix that travels away from the swirler toward the combustion chamber, and b) a counter-flow inside flow (a) created by a low pressure adjacent flow (a). The counter-flow is generally toward the swirler away from the combustion chamber. |
