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). <EOS>