Dry low NOx single stage dual mode combustor construction for a gas turbine
AssigneeGeneral Electric Company
InventorsRichard Borkowicz, David T. Foss, Daniel M. Popa, Warren J. Mick, Jeffery A. Lovett
Life of this patent
Estimating the term…
Abstract
In a gas turbine (10), a plurality of combustors (14), each having a plurality of fuel nozzles (32) arranged about a longitudinal axis of the combustor, and a single combustion zone (70), each fuel nozzle having a diffusion passage (74) and a premix passage (60), the premix passage communicating with a plurality of premix fuel distribution tubes (66) located within a dedicated premix tube (46) adapted to mix the premix fuel and combustion air prior to entry into the single combustion zone (70) located downstream of the premix tube (46).
Claims12
In a gas turbine, a plurality of combustors, each having a plurality of fuel nozzles arranged about a longitudinal axis of the combustor, and a single combustion zone, each fuel nozzle having a diffusion gas passage connected to a diffusion gas inlet and a premix gas passage connected to a premix gas inlet, the premix gas passage communicating with a plurality of premix fuel distribution tubes extending radially away from said premix gas passage, and located within a dedicated premix tube adapted to mix premix fuel and combustion air prior to entry into the single combustion zone located downstream of the premix tube, and wherein said diffusion gas passage terminates at a forwardmost discharge end of said fuel nozzle downstream of said premix fuel distribution tubes but within said dedicated premix tube, and wherein said plurality of radially extending premix fuel distribution tubes are located upstream of said forwardmost end.
A single stage, dual mode gas turbine combustor comprising:
- a combustor casing having an open forward end and an end cover assembly secured to a rearward end thereof;
- a flow sleeve mounted within said casing;
- a sleeve cap assembly secured to said casing and located axially downstream of said end cover assembly;
- a combustion liner having forward and rearward ends, the rearward end secured to said sleeve cap assembly, said combustion liner having a single combustion zone;
- a plurality of fuel nozzle assemblies arranged in a circular array about a longitudinal axis of the combustor, and extending from said end cover assembly and through said sleeve cap assembly, each fuel nozzle assembly including a diffusion gas fuel passage and a premix gas fuel passage;
- and
- a plurality of premix tubes secured to said sleeve cap assembly, each premix tube surrounding a forward portion of a corresponding one of said fuel nozzle assemblies including a plurality of premix gas distribution tubes;
- and
- flow path means for permitting air to flow through said premix tubes in an upstream to downstream direction, past said premix gas distribution tubes to a burning zone in said liner downstream of said premix tubes.
Dependencies are inferred from the claim text.