A combustor liner assembly (108; 110) for a gas turbine engine, comprising a first liner panel (118; 132) having a first forward end (172; 188) and a first aft end; a second liner panel (120; 134) having a second forward end and a second aft end (170; 190); and a support band (114; 116) having a plurality of circumferentially spaced holes (150; 160), the support band (114; 116) arranged between the first liner panel (118; 132) and the second liner panel (120; 134), the support band (114; 116) has a protrusion (155; 165) with a first angled surface (154; 164) and a second angled surface (156; 166), the second angled surface (156; 166) in engagement with the first aft end and the first angled surface (154; 164) in engagement with the second forward end, wherein the first aft end is angled with respect to an inner surface of the first liner panel (118; 132) and the second forward end is angled with respect to a second inner surface of the second liner panel (120; 134), wherein the first aft end and the second forward end each have an angle between 30° and 60°, characterised in that the first aft end and the second forward end each have a plurality of grooves, wherein the grooves are spaced circumferentially along the first aft end and second forward end respectively to form a scallop pattern, wherein the grooves on the first aft end are aligned with the grooves on the second forward end, and wherein the grooves are aligned with the circumferentially spaced holes (150; 160), wherein the first forward end (172; 188) and the second aft end (170; 190) are angled and form a partially conical shape for engagement with the first angled surface (154; 164) and the second angled surface (156; 166), wherein the first angled surface (154; 164) and the second angled surface (166; 166) provide a wavy shape that provides partially conical portions for engagement with the angled ends (194; 196). a first liner panel (118; 132) having a first forward end (172; 188) and a first aft end; a second liner panel (120; 134) having a second forward end and a second aft end (170; 190); and a support band (114; 116) having a plurality of circumferentially spaced holes (150; 160), the support band (114; 116) arranged between the first liner panel (118; 132) and the second liner panel (120; 134), the support band (114; 116) has a protrusion (155; 165) with a first angled surface (154; 164) and a second angled surface (156; 166), the second angled surface (156; 166) in engagement with the first aft end and the first angled surface (154; 164) in engagement with the second forward end, wherein the first aft end is angled with respect to an inner surface of the first liner panel (118; 132) and the second forward end is angled with respect to a second inner surface of the second liner panel (120; 134), wherein the first aft end and the second forward end each have an angle between 30° and 60°, characterised in that the first aft end and the second forward end each have a plurality of grooves, wherein the grooves are spaced circumferentially along the first aft end and second forward end respectively to form a scallop pattern, wherein the grooves on the first aft end are aligned with the grooves on the second forward end, and wherein the grooves are aligned with the circumferentially spaced holes (150; 160), wherein the first forward end (172; 188) and the second aft end (170; 190) are angled and form a partially conical shape for engagement with the first angled surface (154; 164) and the second angled surface (156; 166), wherein the first angled surface (154; 164) and the second angled surface (166; 166) provide a wavy shape that provides partially conical portions for engagement with the angled ends (194; 196).