System and apparatus for combustion swirler anti-rotation
A swirler comprising an anti-rotation feature is provided. The swirler may be installed on a combustor within a gas turbine engine. The swirler may comprise a generally cylindrical profile. In this regard, the swirler may be configured to provide a generally uniform profile within the combustor. The swirler may comprise a floating collar with an anti-rotation feature. The swirler may also include a collar end plate that defines a slot that at least partially encloses the anti-rotation feature and minimizes rotational movement of the floating collar.
1. A combustor, comprising:
a fuel injector;
a combustion chamber configured to receive fuel from the fuel injector; and
a swirler comprising a floating collar comprising an anti-rotation feature and a collar end plate defining a notch;
wherein the swirler is installable on the fuel injector;
wherein the swirler is configured to deliver atomized fuel to the combustion chamber;
wherein the notch is defined as a channel having four sides within the collar end plate;
and
wherein the swirler has a cylindrical profile and the anti-rotation feature does not protrude beyond the cylindrical profile of the swirler.
2. The combustor of claim 1 , wherein the combustor is an axial flow combustor.
3. The combustor of claim 1 , wherein the combustor defines the combustion chamber.
4. A gas turbine engine, comprising:
a compressor,
a turbine configured to drive the compressor; and
a combustor configured to drive the turbine, the combustor comprising:
an injector;
a combustion chamber defined by the combustor and configured to receive fuel from the injector; and
a swirler comprising a floating collar comprising an anti-rotation feature and a collar end plate defining a slot, the anti-rotation feature being retained within the slot;
wherein the swirler is installed on the injector;
wherein the swirler is configured to conduct and atomize fuel to the combustion chamber;
wherein the slot is defined as a channel having four sides; and
wherein the swirler has a cylindrical profile and the anti-rotation feature does not protrude beyond the cylindrical profile of the swirler.
5. The gas turbine engine of claim 4 , wherein the combustor is an axial flow combustor.
6. The gas turbine engine of claim 4 , wherein the swirler comprises a uniform outer profile.
7. The gas turbine engine of claim 4 , wherein the collar end plate minimizes rotation of the floating collar within the swirler.
8. The gas turbine engine of claim 7 , wherein the floating collar is configured to couple to a portion of the injector.
9. The gas turbine engine of claim 7 , wherein the collar end plate is configured to allow radial motion.
10. A swirler, comprising:
a housing defining a volume;
a floating collar contained within the volume defined by the housing, the floating collar comprising an anti-rotation feature; and
a collar end plate operatively coupled to the housing and configured to contain the floating collar within the volume;
wherein the collar end plate defines a channel that is configured to receive the anti-rotation feature and to limit rotational movement of the floating collar;
wherein the swirler has a cylindrical profile;
wherein the channel is defined as a slot having four sides;
wherein the anti-rotation feature does not protrude beyond the cylindrical profile of the swirler.
11. The swirler of claim 10 , wherein the swirler is installable on an injector of a gas turbine engine.
12. The swirler of claim 10 , wherein a first side, a second side, and, a third side define the channel formed in the collar end plate.
13. The swirler of claim 12 , wherein a fourth side defines the channel in the collar end plate.