CMC BOAS with internal support structure

1. A blade outer air seal, comprising:

a base portion extending between a first circumferential side and a second circumferential side and from a first axial side to a second axial side;

a first wall axially spaced from a second wall, the first and second walls extending from the base portion to an outer wall, wherein first and second cutouts are each formed in the first wall and the outer wall, the first cutout arranged near the first circumferential side, and the second cutout arranged near the second circumferential side; and

a rib extending from the base portion to the outer wall spaced axially between the first and second walls, wherein a slot is formed in the second wall between the base portion and the outer wall.

2. The blade outer air seal of claim 1 , wherein the rib extends from the first circumferential side to the second circumferential side.

3. The blade outer air seal of claim 1 , wherein the first and second walls extend from the first circumferential side to the second circumferential side.

4. The blade outer air seal of claim 1 , wherein the rib is arranged at an angle relative to the first wall.

5. The blade outer air seal of claim 4 , wherein the angle is less than 45°.

6. The blade outer air seal of claim 5 , wherein the angle is less than 30°.

7. The blade outer air seal of claim 1 , wherein a first passage is defined between the rib and the first wall and a second passage is defined between the rib and the second wall.

8. The blade outer air seal of claim 7 , wherein the first passage is configured to have a first pressure and the second passage is configured to have a second pressure that is lower than the first pressure.

9. The blade outer air seal of claim 7 , wherein the first passage has a trapezoidal shape.

10. The blade outer air seal of claim 1 , wherein the first and second cutouts form mating surfaces configured to engage a support structure.

11. The blade outer air seal of claim 1 , wherein at least one metering hole extends through the rib.

12. The blade outer air seal of claim 1 , wherein the base portion, the first and second walls, and the outer wall have the same thickness.

13. The blade outer air seal of claim 1 , wherein the blade outer air seal is a ceramic matrix composite material.

14. A turbine section for a gas turbine engine, comprising:

a turbine blade extending radially outwardly to a radially outer tip and for rotation about an axis of rotation;

a blade outer air seal having a plurality of segments mounted in a support structure and arranged circumferentially about the axis of rotation and radially outward of the outer tip; and

wherein each segment has a first wall axially spaced from a second wall, the first and second walls joined to a base portion and an outer wall, and a rib extending from the base portion to the outer wall spaced axially between the first and second walls, and wherein each segment has first and second cutouts in the first wall and the outer wall, the first and second cutouts engaged with the support structure, wherein a slot is formed in the second wall between the base portion and the outer wall.

15. The turbine section of claim 14 , wherein each segment has a second slot in the second wall, the slot and the second slot engaged with the support structure.

16. The turbine section of claim 14 , wherein a first passage is defined between the rib and the first wall and a second passage is defined between the rib and the second wall, and the first passage has a trapezoidal shape.

17. The turbine section of claim 14 , wherein a feather seal is arranged along a circumferential side of each segment, the feather seal extending along an axial length of each segment, the feather seal having a radially extending portion that engages the rib.