Methods and apparatus for cooling gas turbine engine combustors
AssigneeGeneral Electric Company
InventorsCraig Douglas Young, Paul Edward Sabla, Steven Clayton Vise
Life of this patent
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Abstract
A one-piece deflector-flare cone assembly for a gas turbine engine combustor that facilitates extending a useful life of the combustor in a cost-effective and reliable manner is described. The one-piece assembly includes a deflector portion and a flare cone portion. The deflector portion includes an integral opening that extends through the deflector portion for receiving cooling fluid therein. The cooling opening extends circumferentially within the deflector portion. Cooling fluid discharged from the cooling opening is used for film cooling a portion of the deflector portion to facilitate reducing an operating temperature and extending a useful life of the combustor.
Claims20
A method for operating a gas turbine engine including a combustor, the combustor having a centerline axis and including an air swirler and a dome assembly circumferentially around the air swirler, and including an integral slot extending substantially circumferentially around and angled with respect to the centerline axis, said method comprising the steps of:
- supplying fuel to the combustor through the air swirler;
- directing cooling fluid substantially circumferentially and radially outwardly through the dome assembly slot for film cooling at least a portion of the dome assembly.
A combustor for a gas turbine engine, said combustor having a centerline axis and comprising:
- an air swirler;
- and
- a dome assembly circumferentially around said air swirler, said dome assembly comprising an integral slot extending substantially around and angled with respect to the centerline axis, said slot positioned such that cooling fluid is discharged radially outwardly therefrom for film cooling at least a portion of said dome assembly, said slot extending substantially circumferentially within said dome assembly.
A gas turbine engine comprising a combustor having a centerline axis and comprising an air swirler and a dome assembly, said dome assembly configured to secure said air swirler within said combustor, said air swirler within said dome assembly, at least one of said dome assembly and said air swirler comprising a slot extending substantially around and angled with respect to the centerline axis, said slot positioned such that cooling fluid is discharged radially outwardly therefrom for film cooling at least a portion of said dome assembly.
Dependencies are inferred from the claim text.