Partial arc gutter for gas turbine engine

1. A gas turbine engine, comprising:

a bearing compartment;

a seal assembly configured to establish a seal of the bearing compartment, the seal assembly including a seal plate; and

a gutter configured to collect oil slung from the seal plate, wherein the gutter extends only partially around the seal plate.

2. The gas turbine engine as recited in claim 1 , wherein the gutter is at least partially radially outward of the seal plate.

3. The gas turbine engine as recited in claim 1 , wherein the gutter includes an inlet section, a main passageway, and an outlet.

4. The gas turbine engine as recited in claim 3 , wherein the inlet section is configured to direct oil slung from the seal plate into the main passageway.

5. The gas turbine engine as recited in claim 4 , wherein the inlet section includes at least one vane configured to encourage oil to flow into the main passageway.

6. The gas turbine engine as recited in claim 4 , wherein the inlet section has a radially-open cross-section and is concave in cross-section when viewed from an axis of rotation of the seal plate.

7. The gas turbine engine as recited in claim 5 , wherein the inlet section includes a first radially-extending wall, a second radially-extending wall spaced-apart from the first radially extending wall, and an axially-extending wall connecting radially-outer ends of first and second radially-extending walls.

8. The gas turbine engine as recited in claim 5 , wherein the inlet section is arcuate and follows a radius having an origin about the axis of rotation of the seal plate.

9. The gas turbine engine as recited in claim 7 , wherein the inlet section extends circumferentially about the axis of rotation of the seal plate from a first circumferential location to a second circumferential location spaced-apart from the first circumferential location in a direction of rotation of the seal plate.

10. The gas turbine engine as recited in claim 9 , wherein the first circumferential location is spaced-apart from the second circumferential location by less than 180°.

11. The gas turbine engine as recited in claim 10 , wherein the first circumferential location is spaced-apart from the second circumferential location by about 90°.

12. The gas turbine engine as recited in claim 9 , wherein an oil nozzle configured to direct oil onto the seal plate is circumferentially spaced-apart from the first location in a direction opposite the direction of rotation of the seal plate.

13. The gas turbine engine as recited in claim 9 , wherein:

the main passageway begins at the second circumferential location, and

the main passageway includes a radially-closed cross-section.

14. The gas turbine engine as recited in claim 13 , wherein the main passageway includes a first straight section extending from the second circumferential location to a third location.

15. The gas turbine engine as recited in claim 14 , wherein the main passageway includes a curved section between the third location and a fourth location spaced-apart circumferentially from the third location.

16. The gas turbine engine as recited in claim 15 , wherein the main passageway includes a second straight section between the fourth location and the outlet.

17. A method, comprising:

rotating a seal plate of a seal assembly for a bearing compartment of a gas turbine engine;

slinging oil from the seal plate;

capturing the oil slung from the seal plate in a gutter extending only partially around the seal plate.

18. The method as recited in claim 17 , wherein the oil slung from the seal plate is captured by an inlet section of the gutter having a radially-open cross-section.

19. The method as recited in claim 18 , further comprising directing oil from the inlet section to a main passageway of the gutter having a radially-closed cross-section.

20. The method as recited in claim 19 , further comprising draining oil out an outlet of the gutter.