초록 ▼

A premixer for a combustor system has a venturi-type mixing tube with a flow axis, an inlet adjacent one axial mixing tube end, and a nozzle assembly at the opposite axial mixing tube end. The mixing tube inlet is flow connected to a source of compressed air and a source of fuel, and the mixing tube

A premixer for a combustor system has a venturi-type mixing tube with a flow axis, an inlet adjacent one axial mixing tube end, and a nozzle assembly at the opposite axial mixing tube end. The mixing tube inlet is flow connected to a source of compressed air and a source of fuel, and the mixing tube is connected to combustion chamber, an annular or can-type liner and an inlet, and the nozzle assembly extends into the combustion chamber and has at least one port for distributing the fuel/air mixture within a single stage combustion zone. In a preferred configuration, a pair of premixers are located at diametrically opposed positions on an annular combustion chamber, and the venturi axes are both radially disposed and axially inclined with respect to the combustion chamber axis. A single, centrally located, cylindrical air valve controls compressed air flow to both premixers through a manifold and distribution conduits.

대표청구항 ▼

[ What is claimed:] [1.]1. A combustor system for operation with a source of compressed air and a source of fuel, the combustor system comprising:a cylindrical liner defining a single stage combustion chamber, the liner having an axis and having one or more inlets adjacent one axial chamber end, the

[ What is claimed:] [1.]1. A combustor system for operation with a source of compressed air and a source of fuel, the combustor system comprising:a cylindrical liner defining a single stage combustion chamber, the liner having an axis and having one or more inlets adjacent one axial chamber end, the portion of the chamber adjacent the one axial chamber end comprising a single stage combustion zone; andone or more fuel/air premixers each having an inlet for receiving compressed air, an inlet for receiving fuel, and a mixing tube for mixing the received compressed air and fuel and for delivering a fuel/air mixture to the combustion zone through a respective liner inlet, wherein essentially all air for combustion is delivered to the combustion zone solely through said one or more fuel/air premixers,wherein the mixing tube has a flow axis, an inlet adjacent one mixing tube axial end, and a nozzle at an opposite mixing tube axial end, the mixing tube inlet being flow connected to the compressed air inlet and the fuel inlet, and the nozzle extending into the combustion chamber and having one or more ports for distributing the fuel/air mixture within the combustion zone at an angle relative to the mixing tube axis.