초록 ▼

A method facilitates assembling a combustor for a gas turbine engine, wherein the combustor includes a swirler assembly. The method comprises machining material to form a domeplate, positioning a sealplate including an overhanging portion against the domeplate, securing the sealplate in position rel

A method facilitates assembling a combustor for a gas turbine engine, wherein the combustor includes a swirler assembly. The method comprises machining material to form a domeplate, positioning a sealplate including an overhanging portion against the domeplate, securing the sealplate in position relative to the domeplate with a welding process, and welding the swirler assembly to the domeplate.

대표청구항 ▼

What is claimed is: 1. A combustor for a gas turbine engine, said combustor comprising: a swirler assembly; and a dome assembly comprising a sealplate and a domeplate, said sealplate comprising an overhang portion and an integrally-formed body, said sealplate welded to said domeplate such that an a

What is claimed is: 1. A combustor for a gas turbine engine, said combustor comprising: a swirler assembly; and a dome assembly comprising a sealplate and a domeplate, said sealplate comprising an overhang portion and an integrally-formed body, said sealplate welded to said domeplate such that an annular gap is defined between said domeplate and said sealplate overhang portion, said swirler assembly welded to said dome assembly. 2. A combustor in accordance with claim 1 wherein said domeplate comprises an upstream side, a downstream side, and an opening extending therebetween, at least one of said upstream and downstream sides comprises a chamfered edge that defines said opening. 3. A combustor in accordance with claim 1 wherein said domeplate comprises an upstream side, a downstream side, and an opening extending therebetween, at least one of said domeplate upstream and downstream sides comprises a counter-bored edge that defines said opening. 4. A combustor in accordance with claim 3 wherein at least a portion of said sealplate is secured within said counter-bored edge, said counter-bored edge facilitates aligning said swirler assembly relative to said domeplate. 5. A combustor in accordance with claim 1 further comprising a baffle brazed to said sealplate. 6. A combustor in accordance with claim 1 wherein said swirler assembly comprises at least a secondary swirler welded to said sealplate and a primary swirler coupled to said secondary swirler such that said primary swirler is free to move against said secondary swirler. 7. A gas turbine engine comprising a combustor comprising a dome assembly, at least one injector, and a swirler assembly, said dome assembly comprising a sealplate and a domeplate, said sealplate comprising a body and an overhang portion extending integrally from said body, said sealplate welded to said domeplate such that an annular gap is defined between said domeplate and said sealplate overhang portion, said swirler assembly welded to said dome assembly, said at least one injector coupled to said dome assembly. 8. A gas turbine engine in accordance with claim 7 wherein said domeplate comprises an upstream side, a downstream side, and an opening extending therebetween, said opening sized to receive at least a portion of said swirler assembly therethrough, at least one of said domeplate upstream and downstream sides comprises a chamfered edge that circumscribes said opening such that said edge defines said opening. 9. A gas turbine engine in accordance with claim 7 wherein said domeplate comprises an upstream side, a downstream side, and an opening extending therebetween, said opening sized to receive at least a portion of said swirler assembly therethrough, at least one of said domeplate upstream and downstream sides comprises a counter-bored edge that circumscribes said opening such that said edge defines said opening. 10. A gas turbine engine in accordance with claim 8 wherein said counter-bored edge is sized to receive at least a portion of said sealplate therein such that said counter-bored edge facilitates aligning said swirler assembly relative to said domeplate. 11. A gas turbine engine in accordance with claim 7 wherein said combustor further comprises a baffle welded to said sealplate and extending downstream from said domeplate. 12. A gas turbine engine in accordance with claim 7 wherein said swirler assembly comprises at least a secondary swirler welded to said sealplate and a primary swirler coupled to said secondary swirler.