Radial inlet swirler with twisted vanes for fuel injector
AssigneeUnited Technologies Corporation
InventorCharles B. Graves
Life of this patent
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Abstract
The fuel injector for a combustor of a gas turbine engine of the high shear design type is configured to include two swirlers with passages where the vanes in the inner swirler of the inner swirler in the passage which is closest to the centerline of the fuel nozzle includes a judiciously located twist and together with the proper flow ratio between the two swirl passages and the proper swirl angle of the flow stream in each of the passages provide an enhanced fuel injector with improved lean blowout and high altitude relight characteristics while assuring a stable recirculation region in the combustion zone.
Claims14
A high shear designed fuel injector for a combustor of a gas turbine engine comprising a fuel nozzle supported at an inlet of said combustor, a first radial inlet swirler mounted on said fuel nozzle and including a first passage for flowing air into the combustor and being coaxially disposed relative to said fuel nozzle, a second radial inlet swirler mounted adjacent to said first radial swirler and including a second passage for flowing additional air into the combustor and being concentrically disposed relative to said first passage, said first radial inlet swirler having circumferentially disposed vanes, said vanes having a top section and a base section each having a swirl angle, the base section being attached to a radially extending wall of said first or second passage, said vanes being configured with a twist, said twist being about a central axis extending from and changing the swirl angle from the top section to the base section to offset the swirl to a higher level that the swirl would be without twisting the vanes to produce a Rankine vortex.
A high shear designed fuel injector for a combustor of a gas turbine engine comprising a fuel nozzle mounted in a front end of said combustor, a first radial inlet swirler including a first passage for flowing air into the combustor and being coaxially disposed relative to said fuel nozzle and supported thereto, a second radial inlet swirler including a second passage for flowing additional air into the combustor and being concentrically disposed relative to said first passage and being mounted thereto, said first swirler having circumferentially disposed vanes having a top section and a base attached to a radially extending wall of said first or second passage, said vanes being configured with a twist extending from the top section to said base, the base having a vane angle substantially equal to 16.degree. and the twist having an angular spread of 8.degree. above said base for producing a Rankine vortex.
Dependencies are inferred from the claim text.