General Electric Company

Richard J Borkowicz

Masayoshi Kuwata

L Berkley Davis

Warren James Mick

Jeffery Allan Lovett

Daniel Michael Popa

David T Foss

Cheryl Mele

An improved gas turbine combustor of the type including primary and secondary combustion chambers with a venturi including a throat portion located therebetween; a plurality of primary fuel injection nozzles secured to a combustor cap in an annular array upstream of the primary combustion chamber; and a centerbody including a secondary fuel nozzle, said centerbody extending from said combustor cap to said secondary combustion chamber; the improvement comprising a plurality of tertiary fuel injection nozzles arranged in a circular array about a longitudinal axis of the combustor, at a downstream of said venturi throat portion, for injecting fuel into the secondary combustion chamber.

Tertiary fuel, injection system for use in a dry low NOx combustion

An improved gas turbine combustor of the type including primary and secondary combustion chambers with a venturi including a throat portion located therebetween; a plurality of primary fuel injection nozzles secured to a combustor cap in an annular array upstream of the primary combustion chamber; and a centerbody including a secondary fuel nozzle, said centerbody extending from said combustor cap to said secondary combustion chamber; the improvement comprising a plurality of tertiary fuel injection nozzles arranged in a circular array about a longitudinal axis of the combustor, at a location downstream of said venturi throat portion, for injecting fuel into the secondary combustion chamber.

Tertiary fuel injection system for use in a dry low NOx combustion system

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).

Dry low NOx single stage dual mode combustor construction for a gas

A secondary nozzle for a gas turbine includes an elongated, tubular nozzle body having an inlet end and an outlet end; a tubular core assembly having an outer diameter less than an interior diameter of the tubular nozzle body to thereby define a diffusion fuel passage between the core assembly and the tubular nozzle body extending to the outlet end, and a premix fuel passage through the core assembly extending to a pilot orifice at the outlet end; an air passage located along at least a portion of the tubular nozzle body and located radially between the diffusion and premix fuel passages; and, a plurality of gas injectors extending radially out of the elongated tubular nozzle body from the premix fuel passage.

Two stage (premixed/diffusion) gas only secondary fuel nozzle

A dual mode, dual stage low NOx combustor, includes a primary combustion chamber and a secondary combustion chamber separated by a throat region of reduced diameter. Fuel is input into the primary combustors by an annular array of diffusion type nozzles whereas in accordance with the invention, fuel is input into the secondary combustor by a central combination premix and diffusion nozzle. A premix swirler annulus is located upstream of a plurality of fuel distribution tubes of the combined premix and diffusion nozzle.

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Ballston Spa, NY, United States of America

Richard J Borkowicz