Mount for an airfoil

1. A gas turbine engine defining a radial direction, the engine comprising:

an airfoil positioned within an airflow and extending between a root end and a tip along the radial direction; and

a mount coupled to or formed integrally with the root end of the airfoil for mounting the airfoil to the engine, the mount comprising an outer surface along the radial direction exposed to the airflow and defining an air-cooling channel extending between an inlet and an outlet, the inlet positioned on the outer surface of the mount.

2. The engine of claim 1 , wherein the outlet of the air-cooling channel is also positioned on the outer surface of the mount.

3. The engine of claim 1 , wherein the mount further comprises a scoop configured to direct an airflow into the inlet of the channel.

4. The engine of claim 3 , wherein the scoop is positioned at least partially at a downstream end of the inlet and extends at least partially over the inlet.

5. The engine of claim 1 , wherein the air-cooling channel defined by the mount is a first air-cooling channel of a plurality of air-cooling channels defined by the mount.

6. The engine of claim 1 , wherein the air-cooling channel defines a non-uniform geometry along a length thereof.

7. The engine of claim 1 , wherein the mount is formed through an additive manufacturing process.

8. The engine of claim 1 , wherein the outer surface of the mount defines an airfoil slot for receiving the root end of the airfoil, and wherein the air-cooling channel extends generally parallel to the airfoil slot.

9. The engine of claim 1 , wherein the outer surface of the mount defines an airfoil slot for receiving the root end of the airfoil, wherein the air-cooling channel defined by the mount is a first air-cooling channel, wherein the mount further defines a second air-cooling channel extending from an inlet positioned on the outer surface of the mount, and wherein the inlet of the first air-cooling channel is positioned opposite the airfoil slot from the inlet of the second air-cooling channel.

10. The engine of claim 1 , wherein the gas turbine engine is a single unducted rotor engine.

11. The engine of claim 10 , wherein the airfoil is an unducted fan blade of an unducted fan of the single unducted rotor engine.

12. The engine of claim 11 , further comprising:

a stage of unducted guide vanes positioned downstream of the unducted fan.

13. The engine of claim 12 , wherein the stage of unducted guide vanes includes between five and thirty guide vanes.

14. The engine of claim 11 , wherein the unducted fan includes between three and twenty unducted fan blades.

15. A mount for coupling to a root end of an airfoil of a gas turbine engine to mount the airfoil within an airflow of the gas turbine engine, the mount comprising:

a body, the body of the mount comprising an outer surface along a radial direction configured to be exposed to the airflow of the gas turbine engine, the body of the mount defining an air-cooling channel extending between an inlet and an outlet, the inlet positioned on the outer surface of the mount.

16. The mount of claim 15 , wherein the outlet of the air-cooling channel is also positioned on the outer surface of the mount.

17. The mount of claim 15 , wherein the mount further comprises a scoop configured to direct an airflow into the inlet of the channel.

18. The mount of claim 15 , wherein the air-cooling channel defined by the mount is a first air-cooling channel of a plurality of air-cooling channels defined by the mount.

19. The mount of claim 15 , wherein the air-cooling channel defines a non-uniform geometry along a length thereof.

20. The mount of claim 15 , wherein the mount is formed through an additive manufacturing process.