Segmented liner

A component of a turbomachine, the component comprising:

• an outer casing;
• a liner radially inward of the outer casing, the liner comprising a plurality of discrete liner panels;
• a plurality of radial support members extending radially inward from the outer casing;
• and
• a plurality of axial support members disposed proximate to the liner, wherein the plurality of axial support members comprises a plurality of outer axial support members disposed outward of the liner between the liner and the plurality of radial support members along a radial direction and a plurality of inner axial support members disposed inward of the liner along the radial direction.

A gas turbine, comprising:

• a compressor, a combustion section downstream from the compressor, a turbine downstream from the combustion section, an exhaust section downstream from the turbine, and a component, the component comprising:
• an outer casing;
• a liner radially inward of the outer casing, the liner comprising a plurality of discrete liner panels;
• a plurality of radial support members extending radially inward from the outer casing;
• a plurality of axial support members disposed proximate to the liner;
• and
• a bracket mounted to each radial support member of the plurality of radial support members at an end of the radial support member distal from the outer casing, each bracket extending orthogonally to the respective radial support member.