Invention Grant
US08234871B2 Method and apparatus for delivery of a fuel and combustion air mixture to a gas turbine engine using fuel distribution grooves in a manifold disk with discrete air passages 有权
用于使用具有离散空气通道的歧管盘中的燃料分配槽将燃料和燃烧空气混合物输送到燃气涡轮发动机的方法和装置

Method and apparatus for delivery of a fuel and combustion air mixture to a gas turbine engine using fuel distribution grooves in a manifold disk with discrete air passages
Abstract:
A nozzle has combustion air passages extending from a first, upstream end to a second, downstream end. A fuel distribution manifold is associated with the first, upstream end of the nozzle. Combustion air passages correspond to, and align with the air passages in the nozzle. Fuel distribution grooves are formed in one end of the fuel distribution manifold disk and extend from a central opening to the air passages. A fuel circuit cover closes the fuel distribution grooves to define fuel passages that extend from the central opening to the combustion air passages. A fuel supply conduit communicates with the central opening and the fuel passages for delivery of fuel to the combustion air in the air passages.
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