Patent
Gas turbine combustor with turbulence enhanced mixing fuel injectors
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TLDR
In this article, the primary gas fuel spray bars are aerodynamically shaped and a row of fuel discharge ports are formed on opposing sides of the spray bar sides to create turbulence in the air flow that ensures adequate mixing of fuel and air.Abstract:
A combustor for a gas turbine having primary and secondary combustion zones. The combustor has primary gas fuel spray pegs for supplying a lean mixture of gaseous fuel to the primary combustion zone via a first annular pre-mixing passage and secondary fuel spray bars for supplying a lean mixture of fuel to the secondary combustion zone via a second annular pre-mixing passage. The fuel spray bars are aerodynamically shaped and a row of fuel discharge ports are formed on opposing sides of the spray bar. A pair of mixing fins project outwardly from the spray bar sides. The fins create turbulence in the air flow that ensures adequate mixing of the fuel and air. The fins have sufficient height and are displaced sufficiently far from the fuel discharge ports so that although the turbulence has not dissipated by the time the air flow reaches the fuel discharge ports, the zone of recirculation located downstream from the fins does not extend to the fuel discharge ports. This ensures that the spray bars will not act as flame holders and cause combustion to occur prematurely within the pre-mixing passage.read more
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Burner tube and method for mixing air and gas in a gas turbine engine
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Patent
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Byron Andrew Pritchard,Allen Michael Danis,Michael Jerome Foust,Mark David Durbin,Hukam Mongia +4 more
TL;DR: A mixer assembly for use in a combustion chamber of a gas turbine engine is described in this paper, which includes an annular pilot housing having a hollow interior, a fuel nozzle mounted in the housing adapted for dispensing droplets of fuel to the hollow interior of the pilot housing, and a plurality of concentrically mounted axial swirlers positioned upstream from the pilot fuel nozzle.
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Turbine containing system and an injector therefor
TL;DR: In this article, a turbine containing a secondary combustion system is described, which includes an injector for transversely injecting a secondary fuel into a stream of combustion products of the primary combustion system, and at least one exit for communication between said fuel mixture passage and said stream of primary combustion products.
References
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Patent
Dry low NOx single stage dual mode combustor construction for a gas turbine
TL;DR: In this article, a gas turbine with a plurality of combustors and a single combustion zone is described, where each fuel nozzle has a diffusion passage (74) and a premix passage (60), communicating with a manifold of premix fuel distribution tubes (66) located within a dedicated premix tube (46) adapted to mix the premix fuels and combustion air prior to entry into the single combust zone.
Patent
Dual fuel ultra-low NOx combustor
TL;DR: In this paper, a pre-mixing zone has three concentric annular passages that surround a central diffusion-type dual fuel nozzle and swirl vanes are arrayed around the inner and outer passages and around each of the fuel nozzles.
Patent
Gas turbine combustor swirl vane arrangement
TL;DR: In this article, a combustor for a gas turbine has a centrally located fuel nozzle and inner, middle and outer concentric cylindrical liners, the inner liner enclosing a primary combustion zone.
Patent
Dual fuel gas turbine combustor
TL;DR: In this paper, a combustor for a gas turbine having primary and secondary combustion zones is presented, where the primary gas fuel spray nozzles are disposed in fan shaped channels that are arranged in a circumferential array and that are connected to the second annular pre-mixing passage.
Patent
Low emission combustion nozzle for use with a gas turbine engine
TL;DR: An injector nozzle (66, 190) having a central axis (68), said injector's central axis comprising means (179) for passing a pilot fuel through the injector manifold during operation thereof; means (186) for introducing a supply of pilot air through the injection manifold, and said supply of air being mixed with the pilot fuel only after exiting the injectors during operation of the manifold as mentioned in this paper.