Hollow plank design and construction for combustor liner
A combustor includes an inner liner and an outer liner defining a combustion chamber. The inner liner includes an inner mesh structure, and a plurality of inner planks mounted to the inner mesh structure. The outer liner includes an outer mesh structure, and a plurality of outer planks mounted to the outer mesh structure. Each of the plurality of inner planks and outer planks includes an inner wall, an outer wall, and lateral walls defining a cavity to allow circulation of airflow within the cavity to cool down the inner wall.
1. A combustor comprising:
an inner liner and an outer liner defining a combustion chamber therebetween,
the inner liner comprising an inner mesh structure, and a plurality of first hot side planks and a plurality of first cold side planks mounted to the inner mesh structure, and
the outer liner comprising an outer mesh structure, and a plurality of second hot side planks and a plurality of second cold side planks mounted to the outer mesh structure,
wherein each of the plurality of first hot side planks and second hot side planks comprises an inner wall, an outer wall, and lateral walls defining a cavity to allow circulation of airflow within the cavity to cool down the inner wall.
2. The combustor according to claim 1 , wherein the outer wall comprises a plurality of outer holes that communicate with the cavity of each of the plurality of first hot side planks and second hot side planks.
3. The combustor according to claim 1 , wherein the inner wall comprises a plurality of inner holes that communicate with the cavity of each of the plurality of first hot side planks and second hot side planks.
4. The combustor according to claim 1 , wherein the outer wall comprises a plurality of outer holes that communicate with the cavity of each of the plurality of first hot side planks and second hot side planks,
the inner wall comprises a plurality of inner holes that communicate with the cavity of each of planks the plurality of first hot side planks and second hot side planks,
the plurality of inner holes in the inner wall of the plurality of first hot side planks and second hot side planks are oblique holes with respect to the inner wall of the plurality of first hot side planks and second hot side planks, and
the plurality of outer holes in the outer wall of the plurality of first hot side planks and second hot side planks are orthogonal holes with respect to the outer wall of the plurality of first hot side planks and second hot side planks.
5. The combustor according to claim 1 , wherein the lateral walls include a plurality of lateral holes that communicate with the cavity of each of the plurality of first hot side planks and second hot side planks.
6. The combustor according to claim 1 , wherein each of the plurality of first hot side planks and second hot side planks comprises a plurality of fins or turbulators provided within the cavity of each of the plurality of first hot side planks and second hot side planks.
7. The combustor according to claim 1 , wherein the inner mesh structure and the outer mesh structure comprise a plurality of structural elements that connect together and having a hollow polygonal shape with a plurality of sides defining a hollow face.
8. The combustor according to claim 7 , wherein the plurality of first hot side planks and second hot side planks have a solid polygonal shape that matches the hollow polygonal shape of the plurality of structural elements.
9. The combustor according to claim 1 , wherein the plurality of first hot side planks and second hot side planks further comprise a metal coated with a ceramic or thermal barrier coating layer.
10. The combustor according to claim 1 , wherein at least one of the plurality of first hot side planks and second hot side planks comprise one or more metal layer, and one or more ceramic or thermal barrier coating layers deposited on opposite surfaces of the one or more metal layers.
11. A turbine engine comprising:
a combustor comprising:
an inner liner and an outer liner defining a combustion chamber therebetween,
the inner liner comprising an inner mesh structure, and a plurality of first hot side planks and a plurality of first cold side planks mounted to the inner mesh structure, and
the outer liner comprising an outer mesh structure, and a plurality of second hot side planks and a plurality of second cold side planks mounted to the outer mesh structure,
wherein each of the plurality of first hot side planks and second hot side planks comprises an inner wall, an outer wall, and lateral walls defining a cavity to allow circulation of airflow within the cavity to cool down the inner wall.
12. The turbine engine according to claim 11 , wherein the outer wall comprises a plurality of outer holes that communicate with the cavity of each of the plurality of first hot side planks and second hot side planks.
13. The turbine engine according to claim 11 , wherein the inner wall comprises a plurality of inner holes that communicate with the cavity of each of the plurality of first hot side planks and second hot side planks.
14. The turbine engine according to claim 11 , wherein the outer wall comprises a plurality of outer holes that communicate with the cavity of each of the plurality of first hot side planks and second hot side planks,
the inner wall comprises a plurality of inner holes that communicate with the cavity of each of the plurality of first hot side planks and second hot side planks, the plurality of inner holes in the inner wall of the plurality of first hot side planks and second hot side planks are oblique holes with respect to the inner wall of the plurality of first hot side planks and second hot side planks, and
the plurality of outer holes in the outer wall of first hot side planks and second hot side planks are orthogonal holes with respect to the outer wall of the plurality of first hot side planks and second hot side planks.
15. The turbine engine according to claim 11 , wherein the lateral walls include a plurality of lateral holes that communicate with the cavity of each of the plurality of first hot side planks and second hot side planks.
16. The turbine engine according to claim 11 , wherein each of the plurality of first hot side planks and second hot side planks comprises a plurality of fins or turbulators provided within the cavity of each of the plurality of first hot side planks and second hot side planks.
17. The turbine engine according to claim 11 , wherein the inner mesh structure and the outer mesh structure comprise a plurality of structural elements that connect together and having a hollow polygonal shape with a plurality of sides defining a hollow face.
18. The turbine engine according to claim 17 , wherein the plurality of first hot side planks and second hot side planks have a filled polygonal shape that matches the hollow polygonal shape of the plurality of structural elements.
19. The turbine engine according to claim 11 , wherein the plurality of first hot side planks and second hot side planks further comprise a metal coated with a ceramic or thermal barrier coating layer.
20. The turbine engine according to claim 11 , wherein at least one of the plurality of first hot side planks and second hot side planks comprises one or more metal layers, and one or more ceramic or thermal barrier coating layers deposited on opposite surfaces of the one or more metal layers.