A combustor for a gas turbine engine comprising: a support shell with an angled shell interface ; a first liner panel mounted to the support shell via a multiple of studs , the first liner panel including a first rail that extends from a cold side of the first liner panel adjacent to the angled shell interface and includes an angled surface (170; 172) with respect to the cold side , wherein the angled surface (170; 172) with respect to the cold side is between about 30-60 degrees; and a second liner panel mounted to the support shell via a multiple of studs , the second liner panel including a second rail that extends from a cold side of the second liner panel adjacent to said first rail , the second rail adjacent to the angled shell interface and includes an angled surface (170; 172) with respect to the cold side , wherein the angled surface (170; 172) with respect to the cold side is non-perpendicular; wherein the first rail and the second rail each includes an angled end surface , wherein each angled end surface interfaces with the angled shell interface wherein the first liner panel is a forward liner panel , the first rail is an aft rail , the second liner panel is an aft liner panel and the second rail is a forward rail ; wherein the forward and aft rails correspond to the forward and aft edges of the aft and forward liner panels respectively; wherein the aft rail has an aft angled surface and the forward rail has a forward angled surface adjacent to the aft angled surface to form an interface passage therebetween; wherein the support shell includes a cooling impingement passage at an apex of the angled shell interface . a support shell with an angled shell interface ; a first liner panel mounted to the support shell via a multiple of studs , the first liner panel including a first rail that extends from a cold side of the first liner panel adjacent to the angled shell interface and includes an angled surface (170; 172) with respect to the cold side , wherein the angled surface (170; 172) with respect to the cold side is between about 30-60 degrees; and a second liner panel mounted to the support shell via a multiple of studs , the second liner panel including a second rail that extends from a cold side of the second liner panel adjacent to said first rail , the second rail adjacent to the angled shell interface and includes an angled surface (170; 172) with respect to the cold side , wherein the angled surface (170; 172) with respect to the cold side is non-perpendicular; wherein the first rail and the second rail each includes an angled end surface , wherein each angled end surface interfaces with the angled shell interface wherein the first liner panel is a forward liner panel , the first rail is an aft rail , the second liner panel is an aft liner panel and the second rail is a forward rail ; wherein the forward and aft rails correspond to the forward and aft edges of the aft and forward liner panels respectively; wherein the aft rail has an aft angled surface and the forward rail has a forward angled surface adjacent to the aft angled surface to form an interface passage therebetween; wherein the support shell includes a cooling impingement passage at an apex of the angled shell interface . <EOS>