Combustor panels and configurations for a gas turbine engine
The present disclosure relates to combustor configurations, panels and components for a gas turbine engine. In one embodiment, a combustor for a gas turbine engine includes a support structure including a plurality of openings and a plurality of panels mounted to the structure. The plurality of panels define a combustion cavity of the combustor. Each panel includes a first wall configured to receive cooling air and a second wall configured to provide air flow for the cavity. The first and second walls form a cavity and include one or more elements for controlling the cooling effectiveness of each panel. Another embodiment is directed to a combustor panel including one or more elements for controlling cooling effectiveness. Another embodiment is directed to a support structure for a combustor of a gas turbine engine. Another embodiment is directed to configurations of panels including single walled portions or single walled panels.
1. A combustor for a gas turbine engine, the combustor comprising:
a support structure including a plurality of openings; and
a plurality of panels mounted to the support structure,
wherein the plurality of panels define a combustion cavity of the combustor, and
wherein each panel is a dual-walled panel having a first wall configured to receive cooling air into a cavity formed between the first wall and a second wall configured to provide an output air flow from the cavity, the cavity including one or more cooling features extending from at least one of the first and second walls for controlling a cooling effectiveness of each panel,
wherein the support structure includes a plurality of lattice structure elements, wherein one or more air pass-throughs are formed as hollow flow passages within the lattice structure elements that supply metered airflow to the combustion cavity.
2. The combustor of claim 1 , wherein the support structure includes one or more sections configured to provide a mounting structure for the plurality of panels, wherein the mounting structure is at least one of an annular, can, and lattice structure.
3. The combustor of claim 1 , wherein the plurality of openings in the support structure allow for primary airflow received by the combustor to be channeled without a pressure drop to the first wall of the plurality of panels.
4. The combustor of claim 1 , wherein panel cavities include cooling features associated with one or more of trips, pedestals, pin fin features and cooling features in general.
5. The combustor of claim 1 , wherein the plurality of panels additionally include one or more single walled panels mounted to the support structure.
6. The combustor of claim 1 , wherein the plurality of panels include one or more single walled portions.
7. The combustor of claim 1 , wherein the dual-walled panel includes a single-walled portion, wherein the single-walled portion transitions into the first wall and the second wall down an axial length of the dual-walled panel.
8. The combustor of claim 6 , wherein the single-walled portion defines a front end/leading edge of the dual-walled panel.
9. A combustor panel arrangement for a gas turbine engine, the combustor panel arrangement comprising:
a first dual-walled panel having a first wall configured to receive air flow for the combustor panel and a second wall configured to provide an output air flow from a cavity formed between the first and second walls;
one or more cooling features extending from at least one of the first and second walls for controlling a cooling effectiveness between the first and second wall of the first dual-walled panel;
a second dual-walled panel having a first wall configured to receive air flow for the combustor panel and a second wall configured to provide an output air flow from a cavity formed between the first and second walls;
one or more cooling features extending from at least one of the first and second walls for controlling a cooling effectiveness between the first and second wall of the second dual-walled panel; and
a support structure including a plurality of lattice structure elements, wherein one or more air pass-throughs are formed as hollow flow passages within the lattice structure elements that supply metered airflow to a combustion cavity, wherein the first dual-walled panel and the second dual-walled panel are mounted to the support structure.
10. The combustor panel arrangement of claim 9 , wherein the support structure includes one or more sections configured to provide a mounting structure for the panels, wherein the mounting structure is at least one of an annular, can, and lattice structure.
11. The combustor panel arrangement of claim 9 , wherein each panel receives air flow from a plurality of openings in the support structure and channels airflow into the combustion chamber.
12. The combustor panel arrangement of claim 9 , wherein each dual-walled panel is configured with a particular cooling effectiveness, and wherein the cooling features are one or more of trips, pedestal, and pin fin features.
13. The combustor panel arrangement of claim 9 , wherein each panel is configured to engage with the feather seals along lateral surfaces of each panel.
14. The combustor panel of claim 9 , wherein the dual-walled panel includes a single-walled portion, wherein the single-walled portion transitions into the first wall and the second wall down an axial length of the dual-walled panel.
15. A structure for a combustor of a gas turbine engine, the structure comprising:
a support structure including a plurality of openings and comprising a metal structural lattice; and
a plurality of retaining elements configured to retain and secure a plurality of panels to the support structure to define a combustion cavity of the combustor, wherein the plurality of retaining elements comprise at least one alignment pin and at least one holding feature,
wherein the support structure includes a plurality of lattice structure elements, wherein one or more air pass-throughs are formed as hollow flow passages within the lattice structure elements that supply metered airflow to the combustion cavity.
16. The structure of claim 15 , wherein the plurality of openings in the support structure allow for primary airflow received by the combustor to be channeled without a pressure drop into the plurality of panels.
17. The structure of claim 15 , wherein the support structure is a mounting structure for panels of the combustor cavity.
18. The structure of claim 15 , wherein the lattice structure elements include cooling features associated with one or more of trips, pedestal, and pin fin features therein.
19. The structure of claim 15 , further comprising a plurality of dual-walled panels mounted to the plurality of retaining elements, each dual-walled panel having (i) a first wall and a second wall forming a dual-walled portion and (i) a single-walled portion, wherein the single-walled portion transitions into the first wall and the second wall down an axial length of the dual-walled panel.