Abstract: A fuel and gas mixer for a gas turbine combustor includes a body member. The body member has a truncated conical annulus, with its smaller end which communicates with a smaller end of a downstream truncated conical chamber. Gaseous fuel is injected into the annulus through hollow spokes arranged radially in the annulus and mixes with air flow introduced from air upstream passages. The velocity of the primary mixture of the fuel and air in the annulus increases when the flow is directed towards the downstream chamber because the truncated conical shape of the annulus reduces the cross-section of the flow passageway downstream-wise. With increased velocity, the primary mixture is diffused when entering the truncated conical chamber and is further mixed with air introduced from downstream air passages.

Abstract: A fuel and gas mixer for a gas turbine combustor includes a body member. The body member has a truncated conical annulus, with its smaller end which communicates with a smaller end of a downstream truncated conical chamber. Gaseous fuel is injected into the annulus through hollow spokes arranged radially in the annulus and mixes with air flow introduced from air upstream passages. The velocity of the primary mixture of the fuel and air in the annulus increases when the flow is directed towards the downstream chamber because the truncated conical shape of the annulus reduces the cross-section of the flow passageway downstream-wise. With increased velocity, the primary mixture is diffused when entering the truncated conical chamber and is further mixed with air introduced from downstream air passages.

Abstract: A premixer for an industrial type gas turbine engine wherein the premixer includes a diffuser ring assembly made up of annular concentric rings and upstream of the diffuser ring assembly in the airflow path is a corresponding fuel manifold ring assembly, each ring in the manifold ring assembly corresponding to a passageway formed between the diffuser rings, and each manifold ring includes a downstream channel for feeding the fuel to the air as the air passes by the ring.

Abstract: A premixer for an industrial type gas turbine engine wherein the premixer includes a diffuser ring assembly made up of annular concentric rings and upstream of the diffuser ring assembly in the airflow path is a corresponding fuel manifold ring assembly, each ring in the manifold ring assembly corresponding to a passageway formed between the diffuser rings, and each manifold ring includes a downstream channel for feeding the fuel to the air as the air passes by the ring.