Invention Application
US20140311150A1 FUEL NOZZLE FOR A PRE-MIX COMBUSTOR OF A GAS TURBINE ENGINE 有权
燃气涡轮发动机燃油喷嘴

FUEL NOZZLE FOR A PRE-MIX COMBUSTOR OF A GAS TURBINE ENGINE
Abstract:
A fuel nozzle for use in a gas turbine includes a pre-mix flow passage for directing a flow segment of a flow of a working fluid through the fuel nozzle. A first swirler vane and a second swirler vane extend within the pre-mix flow passage. The first swirler vane provides a first wake region within the flow segment. The second swirler vane provides a second wake region within the flow segment. A fuel injection peg is disposed downstream from the first swirler vane and the second swirler vane. The fuel injection peg is positioned within the flow segment between the first wake region and the second wake region.
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