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A swirler for a combustor of a gas turbine engine includes a swirler outer body with a male snap component and/or female snap component of a snap-fit interface defined around a swirler central longitudinal axis. A bulkhead assembly for a combustor of a gas turbine engine includes a swirler mounted t

A swirler for a combustor of a gas turbine engine includes a swirler outer body with a male snap component and/or female snap component of a snap-fit interface defined around a swirler central longitudinal axis. A bulkhead assembly for a combustor of a gas turbine engine includes a swirler mounted to a bulkhead support shell through a snap-fit interface.

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1. A forward assembly for a combustor of a gas turbine engine, the forward assembly comprising: a bulkhead support shell;a swirler mounted to said bulkhead support shell through a snap-fit interface; anda cowl mounted to said bulkhead support shell,wherein said cowl includes a circumferentially dist

1. A forward assembly for a combustor of a gas turbine engine, the forward assembly comprising: a bulkhead support shell;a swirler mounted to said bulkhead support shell through a snap-fit interface; anda cowl mounted to said bulkhead support shell,wherein said cowl includes a circumferentially distributed hood port to extend into contact with said swirler to apply an axial load to said swirler, and said snap-fit interface is located along a frustro-conical surface of said swirler. 2. The forward assembly as recited in claim 1, wherein said swirler includes a male snap component. 3. The forward assembly as recited in claim 2, wherein said bulkhead support shell includes a female snap component around a swirler central longitudinal axis. 4. The forward assembly as recited in claim 3, wherein said male snap component extends radially outward with respect to the swirler central longitudinal axis. 5. The forward assembly as recited in claim 1, wherein said snap-fit interface is located along a swirler outer body. 6. The forward assembly as recited in claim 5, further comprising a swirler inner body mounted within said swirler outer body along a swirler central longitudinal axis. 7. The forward assembly as recited in claim 6, further comprising a guide housing mounted to said swirler inner body. 8. The forward assembly as recited in claim 7, further comprising a capture plate mounted to said guide housing to retain a nozzle guide such that said nozzle guide is movable with respect to said guide housing. 9. The forward assembly as recited in claim 1, wherein said frustro-conical surface of said swirler is defined along a swirler outer body. 10. The forward assembly as recited in claim 9, further comprising a guide housing mounted to a swirler inner body mounted at least partially within said swirler outer body, and a capture plate mounted to said guide housing to retain a nozzle guide such that said nozzle guide is movable with respect to said guide housing. 11. A method of assembling a swirler into a bulkhead support shell of a gas turbine engine, the method comprising: snap fitting at a snap-fit interface the swirler into the bulkhead support shell along a swirler axis; andmounting a cowl to said bulkhead support shell,wherein said cowl includes a circumferentially distributed hood port that extends into contact with the swirler to apply an axial load to the swirler, and the snap-fit interface is located along a frustro-conical surface of the swirler. 12. A forward assembly for a combustor of a gas turbine engine, the forward assembly comprising: a bulkhead support shell;a swirler mounted to said bulkhead support shell through a snap-fit interface located along a frustro-conical surface of said swirler.