| 摘要 |
<p>A fuel/air premixer (16) for an industrial type gas turbine combustor (10) wherein the premixer (16) includes a diffuser ring assembly (20) made up of annular concentric rings (22) and upstream of the diffuser ring assembly (20) in the airflow path is a corresponding fuel manifold ring assembly (32), each ring (34) in the manifold ring assembly (32) corresponding to a passageway formed between the diffuser rings (22), and each manifold ring (34) includes a downstream channel (40) for feeding the fuel to the air as the air passes by the ring (34). The passageways have an upstream section and a downstream section relative to the airflow with a converging cross-sectional area of the upstream and a diverging cross-sectional area at the downstream section.</p> |
