A gas turbine engine , comprising: a compressor section ; a turbine section ; a combustor section having a plurality of combustor assemblies arranged circumferentially about an engine axis (A); at least one of the combustor assemblies having a liner assembly (108; 110) defining a combustion chamber , the liner assembly (108; 110) 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 first and second angled surfaces (154, 156; 164, 166), the first aft end abuts the second angled surface (156; 166) and the second forward end abuts the first angled surface (154; 164); wherein the first aft end of the first liner panel (118; 132) and the second forward end of the second liner panel (120; 134) have a plurality of grooves ; wherein the grooves are spaced circumferentially along the ends to form a scallop pattern; wherein the grooves on the first liner panel (118; 132) and the second liner panel (120; 134) are aligned with one another and with the holes of the support band , such that each hole is aligned with a groove in the circumferential direction, such that the holes on the support band fit within the grooves ; characterized in that the angled ends form a partially conical shape for engagement with the angled surfaces of the support band ; wherein the angled surfaces provide a wavy shape that provides partially conical portions for engagement with the angled ends . a compressor section ; a turbine section ; a combustor section having a plurality of combustor assemblies arranged circumferentially about an engine axis (A); at least one of the combustor assemblies having a liner assembly (108; 110) defining a combustion chamber , the liner assembly (108; 110) 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 first and second angled surfaces (154, 156; 164, 166), the first aft end abuts the second angled surface (156; 166) and the second forward end abuts the first angled surface (154; 164); wherein the first aft end of the first liner panel (118; 132) and the second forward end of the second liner panel (120; 134) have a plurality of grooves ; wherein the grooves are spaced circumferentially along the ends to form a scallop pattern; wherein the grooves on the first liner panel (118; 132) and the second liner panel (120; 134) are aligned with one another and with the holes of the support band , such that each hole is aligned with a groove in the circumferential direction, such that the holes on the support band fit within the grooves ; characterized in that the angled ends form a partially conical shape for engagement with the angled surfaces of the support band ; wherein the angled surfaces provide a wavy shape that provides partially conical portions for engagement with the angled ends . <EOS>