Combustor panel cooling arrangements
Combustors and panels for use in combustor sections of gas turbine engines, the panels having a panel body having a first wall with a first sidewall and a second sidewall extending each extending from the first wall in the same direction at edges of the first wall and a plurality of cavity walls arranged between the first sidewall and the second sidewall and extending from the panel in the direction of the first and second sidewalls, wherein a plurality of cooling cavities are defined by the cavity walls, the first wall, and at least one of the first sidewall and the second sidewall, wherein each cooling cavity extends from an inlet hole to an outlet hole, wherein the outlet hole is formed in the first wall.
1. A combustor panel for use in a gas turbine engine combustor section, the combustor panel comprising:
a panel body having a first wall with a first sidewall and a second sidewall each extending from the first wall in the same direction at respective edges of the first wall; and
a plurality of cavity walls arranged between the first sidewall and the second sidewall and extending from the panel body in the direction of the first and second sidewalls, wherein a plurality of cooling cavities are defined by the cavity walls, the first wall, and at least one of the first sidewall and the second sidewall,
a second wall extending from at least one of the first sidewall and the second sidewall, parallel to the first wall, and defining a wall of the cooling cavities such that the cooling cavities are defined between the cavity walls, the first wall, at least one of the first sidewall and the second sidewall, and the second wall,
wherein each cooling cavity extends from an inlet hole to an outlet hole, wherein the outlet hole is formed in the first wall,
wherein each cooling cavity of the plurality of cooling cavities is fluidly separate from each other cooling cavity of the plurality of cooling cavities, within the panel body, and
wherein a first cooling cavity of the plurality of cooling cavities defines a flow path in a direction from the first sidewall to the second sidewall and a second cooling cavity of the plurality of cooling cavities defines a flow path in a direction from the second sidewall to the first sidewall.
2. The combustor panel of claim 1 , wherein the inlet hole is closer to one of the first sidewall and the second sidewall and the outlet is closer to the other of the first sidewall and the second sidewall.
3. The combustor panel of claim 1 , wherein the inlet hole is an impingement hole and the outlet hole is an effusion hole.
4. The combustor panel of claim 1 , wherein an inlet end of at least one cooling cavity includes a single inlet hole and an outlet end of the of the at least one cooling cavity includes a plurality of outlet holes.
5. The combustor panel of claim 1 , wherein at least one cooling cavity includes one or more augmentation features arranged to control a cooling flow passing through the at least one cooling cavity.
6. The combustor panel of claim 1 , wherein the first and second sidewalls are configured to fixedly attach to a combustor shell.
7. The combustor panel of claim 1 , wherein the first sidewall is an exterior wall of the combustor panel and the second sidewall is interior sidewall that defines a panel aperture.
8. The combustor panel of claim 7 , wherein the outlet holes include first outlet holes arranged adjacent to the first sidewall and second outlet holes arranged adjacent the second sidewall, and wherein the first wall is a solid body between the first outlet holes and the second outlet holes.
9. The combustor panel of claim 1 , wherein the second wall is configured to fixedly attach to a combustor shell.
10. The combustor panel of claim 1 , wherein the second wall varies in thickness such that at least one cooling cavity tapers in a direction from the inlet hole to the outlet hole.
11. The combustor panel of claim 1 , wherein the second wall separates at least one cooling cavity into a first portion and a second portion, wherein the first portion and the second portion of the cooling cavity are fluidly connected by a turn structure.
12. The combustor panel of claim 11 , wherein one or more particle discouragers are arranged on the second wall within the first portion of the cooling cavity.
13. The combustor panel of claim 1 , further comprising a third wall extending from at least one of the first sidewall and the second sidewall and defining a wall of the cooling cavities such that the cooling cavities are defined between the cavity walls, the first wall, at least one of the first sidewall and the second sidewall, the second wall, and the third wall.
14. The combustor panel of claim 13 , wherein the third wall and the second wall define a first portion of at least one cooling cavity and the second wall and the first wall define a second portion of the at least one cooling cavity.
15. A combustor of a gas turbine engine, the combustor comprising:
a combustor shell defining a support structure; and
at least one combustor panel mounted to the support structure, the at least one combustor panel comprising:
a panel body having a first wall with a first sidewall and a second sidewall each extending from the first wall in the same direction at respective edges of the first wall; and
a plurality of cavity walls arranged between the first sidewall and the second sidewall and extending from the panel body in the direction of the first and second sidewalls, wherein a plurality of cooling cavities are defined by the cavity walls, the first wall, and at least one of the first sidewall and the second sidewall,
a second wall extending from at least one of the first sidewall and the second sidewall, parallel to the first wall, and defining a wall of the cooling cavities such that the cooling cavities are defined between the cavity walls, the first wall, at least one of the first sidewall and the second sidewall, and the second wall,
wherein each cooling cavity extends from an inlet hole to an outlet hole, wherein the outlet hole is formed in the first wall,
wherein each cooling cavity of the plurality of cooling cavities is fluidly separate from each other cooling cavity of the plurality of cooling cavities, within the panel body, and
wherein a first cooling cavity of the plurality of cooling cavities defines a flow path in a direction from the first sidewall to the second sidewall and a second cooling cavity of the plurality of cooling cavities defines a flow path in a direction from the second sidewall to the first sidewall.
16. The combustor of claim 15 , wherein the inlet holes are impingement holes in the combustor shell.
17. The combustor of claim 15 , wherein the first sidewall is an exterior wall of the combustor panel and the second sidewall is interior sidewall that defines a panel aperture, wherein the combustor further includes a fuel injector that is installed within the panel aperture.