Premix fuel nozzle internal flow path enhancement
A fuel injection and nozzle technology, applied in the field of gas turbine fuel nozzle structure
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[0020] See figure 1 The gas turbine 10 includes a compressor housing 12 (partially shown), a plurality of combustors 14 (one shown), and a turbine inlet section shown here through a single turbine nozzle blade 16. Although not specifically shown, the turbine blades are drivingly connected to the compressor rotor along a common axis. The compressor pressurizes the inlet air, which then turns and flows in the opposite direction (as indicated by the fluid arrow) into the combustor 14, where it is used to cool the combustor and provide air for the combustion process.
[0021] More specifically, each combustor 14 includes a substantially cylindrical combustor housing 18 that is fixed to the turbine housing 20 by, for example, bolts 22. The front end of the burner housing is closed by an end cover assembly 24. The end cover assembly 24 may include conventional supply pipes, manifolds, and related valves (generally shown at 26), etc., for supplying gas, liquid fuel, and Air (and water ...
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