Patent ID: 6442939
Filing Date: 2002-09-03
Classification: F23D,F23R

Abstract:
A fuel/air premixer for a gas turbine combustor wherein the premixer comprises an annular diffuser assembly placed in the airflow upstream of an inlet to the combustor, the diffuser assembly including a plurality of concentric rings wherein a diffuser passageway is formed between each adjacent ring in a pair of rings; the diffuser assembly has an upstream section and a downstream section relative to the airflow; the passageway formed by a pair of adjacent rings includes a converging cross-sectional area at the upstream section of the diffuser assembly and a diverging area at the downstream section of the diffuser assembly and a gap defined at the narrowest part of the passageway between the upstream and downstream sections; an assembly of concentric fuel manifold rings is located upstream of the diffuser assembly whereby each manifold ring is located in axial alignment with a corresponding diffuser passageway whereby the air flows around the manifold rings and through the corresponding diffuser passageways, and fuel is delivered into the airflow from the manifold rings.