Ceramic combustor liner panel for a gas turbine engine
A combustor assembly includes a support structure and at least one combustor liner panel selectively attached to the support structure. The combustor liner panel includes an uncooled ceramic portion, a cooled ceramic portion and a support that receives the cooled ceramic portion.
1. A combustor support-liner assembly, comprising:
a support structure; at least one combustor liner panel selectively attached to said support structure, wherein said at least one combustor liner panel includes an uncooled ceramic portion, a cooled ceramic portion circumferentially offset from said uncooled ceramic portion and a support that receives said cooled ceramic portion, said uncooled ceramic portion and said cooled ceramic portion positioned at an equal radial distance from a longitudinal centerline axis that extends through said support structure; and
wherein said cooled ceramic portion is oriented generally in-line with a combustor fuel nozzle.
2. The assembly as recited in claim 1 , wherein said cooled ceramic portion includes a groove and said support includes a tongue, and said tongue is selectively received within said groove to mount said cooled ceramic portion to said support.
3. The assembly as recited in claim 1 , wherein each of said uncooled ceramic portion and said cooled ceramic portion are comprised of a ceramic foam.
4. The assembly as recited in claim 1 , wherein said support structure includes a cage assembly having an inner cage and an outer cage, and each of said inner cage and said outer cage include a plurality of combustor liner panels disposed circumferentially about said inner cage and said outer cage, and said combustor liner panels of said inner cage face radially outwardly and said combustor liner panels of said outer cage face radially inwardly.
5. The assembly as recited in claim 1 , comprising a plenum extending between said support structure and said at least one combustor liner panel.
6. The assembly as recited in claim 5 , wherein airflow from said plenum is received by said cooled ceramic portion to cool said cooled ceramic portion.
7. The assembly as recited in claim 5 , comprising a backing layer positioned on a side of said uncooled ceramic portion that faces said plenum, wherein said backing layer blocks airflow from said plenum.
8. A gas turbine engine, comprising:
a compressor section disposed about an engine longitudinal centerline axis;
a turbine section downstream of said compressor section; and
a combustor section positioned between said compressor section and said turbine section and including a support structure and at least one combustor liner panel; and
wherein said at least one combustor liner panel includes an uncooled ceramic portion, a cooled ceramic portion circumferentially offset from said uncooled ceramic portion, and a support that receives said cooled ceramic portion, said uncooled ceramic portion and said cooled ceramic portion positioned at an equal radial distance from a longitudinal centerline axis of the combustor section, said combustor section including at least one fuel nozzle and said cooled ceramic portion is oriented generally in-line with said fuel nozzle.
9. The gas turbine engine as recited in claim 8 , wherein said combustor section includes a plurality of combustor liner panels disposed circumferentially about said engine longitudinal centerline axis.
10. The gas turbine engine as recited in claim 8 , wherein said support is selectively attached to said support structure to support and configure said at least one combustor liner panel relative to said combustor section.
11. The gas turbine engine as recited in claim 8 , comprising a plenum extending between said support structure and said at least one combustor liner panel.