Fuel injector

1. A fuel injector assembly for a gas turbine engine the assembly comprising:

a pilot injector having a central axis;

a main injector located radially outwardly of the pilot injector;

a concentric splitter separating the pilot injector from the main injector and bounding a volume through which in use a fuel injected by the pilot injector flows, the concentric splitter having a cavity,

wherein the splitter has a toroid chamber that is supplied with air in use to generate a toroidal flow, the toroid chamber having an axially rearward surface through which air is supplied to the toroid chamber and an open axially forward surface, and

an aperture that supplies the air and has an axis that extends substantially secantially from the cavity to the toroid chamber.

2. A fuel injector head according to claim 1 , wherein the pilot injector comprises an annular pilot fuel housing having an inner surface and being concentric with the central axis, the inner surface of the fuel housing defining a prefilmer surface for the supply of fuel thereto in the form of a film extending to a prefilmer lip, wherein the inner surface defines a bore for the supply of air over the prefilmer.

3. A fuel injector assembly according to claim 1 , wherein the pilot injector comprises a nozzle located at the central axis for ejecting fuel into the volume.

4. A fuel injector head according to claim 1 , wherein the pilot injector comprises an annular outer bore concentric with the central axis for the supply of air into the volume.

5. A fuel injector according to claim 4 , wherein the splitter has a radially inner surface that defines the radially outer wall of the annular outer bore.

6. A fuel injector according to of claim 1 , wherein the concentric splitter has a radially outer wall, wherein the radially outer wall and the radially inner surface define the cavity.

7. A gas turbine engine incorporating the fuel injector assembly according to claim 1 .

8. A fuel injector according to claim 1 , wherein the aperture has an inlet and an outlet, and the inlet extends from the cavity and the outlet extends from the toroid chamber.

9. A combustor of a gas turbine engine incorporating the fuel injector assembly according to claim 1 .

10. A combustor according to claim 9 , wherein the combustor defines a combustion volume with the open axially forward surface bounding a portion of the combustion volume.

11. A combustor according to claim 10 , wherein the toroid chamber has a circulating flow of air, the air at the axially rearward surface moving in a direction towards the axis and the air at the axially forward open surface moving radially away from the axis.

12. A combustor according to claim 11 , wherein the air at the axially forward open surface sheds to the combustion volume.

13. An annular combustor of a gas turbine engine comprising a fuel injector assembly, the fuel injector assembly further comprising:

a pilot injector having a central axis;

a main injector located radially outwardly of the pilot injector;

a concentric splitter separating the pilot injector from the main injector and bounding a volume through which in use a fuel injected by the pilot injector flows,

wherein the splitter has a toroid chamber that is supplied with air in use to generate a toroidal flow, the toroid chamber having an axially rearward surface through which air is supplied to the toroid chamber and an open axially forward surface,

the annular combustor defines a combustion volume with the open axially forward surface bounding a portion of the combustion volume,

the toroid chamber has a circulating flow of air, the air at the axially rearward surface moving in a direction towards the axis and the air at the axially forward open surface moving radially away from the axis, and

the air at the axially forward open surface sheds to the combustion volume.

14. A combustor according to claim 12 , wherein the combustor is an annular combustor.