Gas turbine engine carburetor
AssigneeGeneral Electric Company
InventorsJohn W. Vinson, Pamela C. Kwong, Paul E. Sabla
Life of this patent
Estimating the term…
Abstract
A gas turbine engine carburetor including an annular swirler and a new and improved fuel injector cooperating therewith is disclosed which is effective for providing low BTU gaseous fuel to a combustor. The swirler includes a plurality of circumferentially spaced swirler vanes effective for channeling air along an annular inner surface of the swirler. The fuel injector includes a hollow injector tip having an aft portion including a plurality of circumferentially spaced outlet apertures disposed in an outer surface thereof. The outer surface is aligned obliquely to a longitudinal centerline axis of the injector tip and the swirler.
Claims25
A carburetor for a gas turbine engine for mixing air with a combustible, gaseous fuel supplied through an inlet, comprising:
- an annular swirler having a first longitudinal centerline axis, an annular inner surface disposed coaxially with respect to said first axis, and a plurality of circumferentially spaced swirler vanes fixedly connected to an upstream end of said inner surface, said swirler vanes being positioned to channel air over said inner surface;
- and
- a fuel injector for injecting only said gaseous fuel, said fuel injector including a hollow injector tip formed as a single annular shell having a second longitudinal centerline axis, said injector tip comprising a substantially cylindrical forward portion including said inlet for receiving said gaseous fuel therethrough at an inlet velocity, and an aft portion having a decreasing cross sectional area in the downstream direction, said tip aft portion having an outer surface directly facing said swirler inner surface and being obliquely aligned at an angle A with respect to said second axis, said angle A being greater than 0 degrees and less than 90 degrees, and said tip aft portion including a plurality of circumferentially spaced outlet apertures disposed in said outer surface for discharging said gaseous fuel therethrough, said outlet apertures directly facing said swirler inner surface and being sized relative to said inlet to reduce the axial velocity of said discharged gaseous fuel below said inlet velocity, and said swirler vanes and said outlet apertures being positioned relative to each other to cause said air channeled over said swirler inner surface to mix substantially only with said discharged gaseous fuel.
A carburetor for a gas turbine engine for mixing air with a combustible, gaseous fuel supplied through an inlet comprising:
- an annual swirler having a first longitudinal centerline axis, an annular inner surface disposed coaxially with respect to said first axis, and a plurality of circumferentially spaced swirler vanes fixedly connected to an upstream end of said inner surface for channeling air over said inner surface;
- a fuel injector for injecting only said gaseous fuel, said fuel injector including a hollow injector tip having a second longitudinal centerline axis aligned coaxially with said first axis, said injector tip including said inlet for receiving said gaseous fuel therethrough at an axial inlet velocity and a conical aft portion having an outer surface directly facing said swirler inner surface, said outer surface decreasing in circumference in a downstream direction and being aligned at an angle A of about 15 degrees with respect to said second axis, said tip aft portion including a plurality of circumferentially spaced triangularly shaped outlet apertures for discharging said gaseous fuel therethrough, said apertures lying substantially in said outer surface and each having a base end positioned adjacent the base of said conical aft section and an apex end facing in a downstream direction therefrom, said outlet apertures being sized relative to said inlet to reduce the axial velocity of the discharged gaseous fuel below said inlet velocity, said apertures directly facing said swirler inner surface to effect further velocity reduction by impingement of said gaseous fuel on said inner surface and by mixing with said air from said swirler vanes.
A gas turbine engine carburetor according to claim 14 wherein said swirler inner surface defines a venturi having a converging portion, said injector tip outlet apertures being oriented to direct said discharged gaseous fuel toward said venturi converging portion for mixing with air from said swirler vanes, and said swirler further including a plurality of circumferentially spaced second swirler vanes for swirling air in a direction opposite to the swirling direction of air from said first vanes, said second vanes being positioned so as to effect further mixing with air downstream from said converging portion.
A fuel injector for a gas turbine engine comprising:
- a gas delivery tube for receiving and channeling only a gaseous fuel;
- a hollow injector tip having a longitudinal centerline axis and an inlet of area B, said inlet being in flow communication with said delivery tube for receiving said gaseous fuel therefrom at an inlet velocity, said injector tip further including an aft end portion having an outer surface decreasing in circumference in a downstream direction, a plurality of circumferentially spaced outlet apertures disposed in said outer surface for discharging said gaseous fuel therethrough, said outlet apertures collectively having a discharge area C, and means for reducing the axial discharge velocity of said gaseous fuel below said inlet velocity wherein area C is greater than area B.
A gas turbine engine carburetor for mixing air with a combustible gaseous fuel comprising:
- an annular swirler having a first longitudinal centerline axis, an annular inner surface disposed coaxially with respect to said first axis, and a plurality of circumferentially spaced swirler vanes fixedly connected to an upstream end of said inner surface for channeling air over said inner surface;
- a fuel injector for injecting only said gaseous fuel and including a hollow injector tip having a second longitudinal centerline axis aligned with said first axis, said tip comprising an inlet for receiving said gaseous fuel at an inlet velocity and a tip aft portion including an outer surface, said outer surface having a plurality of mutually spaced outlet apertures disposed therein for discharging said gaseous fuel therethrough toward said swirler inner surface and to effect mixing with said air from said swirler vanes;
- and
- means for reducing the axial velocity of said gaseous fuel discharged from said outlet apertures below said inlet velocity, said axial velocity being a velocity component in an axial downstream direction parallel to said second longitudinal centerline axis.
Dependencies are inferred from the claim text.