Slot cooled combustor

1. A combustor for use in a gas turbine engine, the combustor enclosing a combustion chamber having a combustion area, wherein the combustor comprises:

an outward shell;

an inward shell located radially inward of the outward shell, the inward shell and the outward shell defining the combustion chamber therebetween;

an aft outward panel located proximate the outward shell, the aft outward panel extending from an aft end of the combustion chamber to an outward panel joint;

an aft inward panel located proximate the inward shell, the aft inward panel extending from the aft end of the combustion chamber to an inward panel joint; and

a forward panel located proximate a forward end of the combustion chamber, the forward panel comprising:

an outward wall located proximate the outward shell;

an inward wall located proximate the inward shell; and

a forward wall located proximate the forward end of the combustion chamber, the forward wall extending from the inward wall to the outward wall,

wherein the outward wall extends from the forward wall to the outward panel joint and an aft portion of the outward wall overlaps the aft outward panel by a first distance at the outward panel joint,

wherein the inward wall extends from the forward wall to the inward panel joint and an aft portion of the inward wall overlaps the aft inward panel by a second distance at the inward panel joint,

wherein the aft outward panel includes an outer fold where the aft outward panel folds over on itself to form a first cavity, the outer fold being located at the outward panel joint where the outward wall overlaps the aft outward panel by the first distance;

wherein a portion of the outer fold is adjacent to the outward shell;

wherein the aft outward panel is configured to be attached to the outward shell using a first bolt that extends through the outward shell and the portion of the outer fold that is adjacent to the outward shell such that a portion of the first bolt is located in the first cavity,

wherein the aft inward panel includes an inner fold where the aft inward panel folds over on itself to form a second cavity, the inner fold being located at the inward panel joint where the inward wall overlaps the aft inward panel by the second distance;

wherein a portion of the inner fold is adjacent to the inward shell, and

wherein the aft inward panel is configured to be attached to the inward shell using a second bolt that extends through the inward shell and the portion of the inner fold that is adjacent to the outward shell such that a portion of the second bolt is located in the second cavity.

2. The combustor of claim 1 , wherein the aft portion of the outward wall is located radially inward from the aft outward panel.

3. The combustor of claim 1 ,

wherein the aft portion of the outward wall and the aft outward panel define an outward air slot therebetween, and

wherein the outward air slot is continuous or intermittent circumferentially around the combustion chamber.

4. The combustor of claim 1 ,

wherein the aft portion of the inward wall and the aft inward panel define an inward air slot therebetween, and

wherein the inward air slot is continuous or intermittent circumferentially around the combustion chamber.

5. The combustor of claim 1 , wherein the forward panel is composed of a ceramic matrix composite.

6. The combustor of claim 1 , wherein the inward aft panel and the outward aft panel are composed of a ceramic matrix composite.

7. The combustor of claim 3 , wherein the outward wall and the outward shell define an outward air passageway therebetween, the outward air passageway being fluidly connected to the outward air slot.

8. The combustor of claim 4 , wherein the inward wall and the inward shell define an inward air passageway therebetween, the inward air passageway being fluidly connected to the inward air slot.

9. The combustor of claim 7 , wherein the outward air slot fluidly connects the outward air passageway to the combustion area.

10. The combustor of claim 8 , wherein the inward air slot fluidly connects the inward air passageway to the combustion area.

11. A method of assembling a combustor, the method comprising:

inserting an inward shell radially inward of the outward shell, the inward shell and an outward shell defining a combustion chamber therebetween;

inserting an aft outward panel into an aft end of the combustion chamber, the aft outward panel being located proximate the outward shell and extending from the aft end of the combustion chamber to an outward panel joint; inserting an aft inward panel into the aft end of the combustion chamber, the aft inward panel being located proximate the inward shell and extending from the aft end of the combustion chamber to an inward panel joint;

inserting a forward panel into a forward end of the combustion chamber, the forward panel being located proximate the forward end of the combustion chamber, the forward panel comprising:

an outward wall located proximate the outward shell;

an inward wall located proximate the inward shell; and

a forward wall located proximate the forward end of the combustion chamber, the forward wall extending from the inward wall to the outward wall,

wherein the outward wall extends from the forward wall to the outward panel joint and an aft portion of the outward wall overlaps the aft outward panel by a first distance at the outward panel joint,

wherein the inward wall extends from the forward wall to the inward panel joint and an aft portion of the inward wall overlaps the aft inward panel by a second distance at the inward panel joint,

wherein the aft outward panel includes an outer fold where the aft outward panel folds over on itself to form a first cavity, the outer fold being located at the outward panel joint where the outward wall overlaps the aft outward panel by the first distance;

wherein a portion of the outer fold is adjacent to the outward shell;

wherein the aft outward panel is configured to be attached to the outward shell using a first bolt that extends through the outward shell and the portion of the outer fold that is adjacent to the outward shell such that a portion of the first bolt is located in the first cavity,

wherein the aft inward panel includes an inner fold where the aft inward panel folds over on itself to form a second cavity, the inner fold being located at the inward panel joint where the inward wall overlaps the aft inward panel by the second distance;

wherein a portion of the inner fold is adjacent to the inward shell; and

wherein the aft inward panel is configured to be attached to the inward shell using a second bolt that extends through the inward shell and the portion of the inner fold that is adjacent to the outward shell such that a portion of the second bolt is located in the second cavity;

inserting the first bolt through the outward shell and the portion of the outer fold that is adjacent to the outward shell such that the portion of the first bolt is located in the first cavity; and

inserting the second bolt through the inward shell and the portion of the inner fold that is adjacent to the inward shell such that the portion of the second bolt is located in the second cavity.

12. The combustor of claim 1 , wherein the outward shell and the inward shell form an outermost shell of the combustion chamber.

13. The combustor of claim 1 , a gas turbine engine comprising the combustor of claim 1 .

14. The combustor of claim 1 , wherein the aft portion of the outward wall and the aft outward panel define an outward air slot therebetween.

15. The combustor of claim 1 , wherein the aft portion of the inward wall and the aft inward panel define an inward air slot therebetween.

16. The combustor of claim 1 , wherein the aft portion of the outward wall is parallel with the aft outward panel.

17. The combustor of claim 1 , wherein the aft portion of the inward wall is parallel with the aft inward panel.

18. The method of claim 11 , wherein the outward shell and the inward shell form an outermost shell of the combustion chamber.