A combustor for a gas turbine engine comprising: a support shell (68,70) with an angled shell interface; a first liner panel (72A,72B) mounted to the support shell (68,70) via a multiple of studs, the first liner panel (72A,72B) including a first rail that extends from a cold side of the first liner panel (72A,72B) 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 (74A,74B) mounted to the support shell (68,70) via a multiple of studs, the second liner panel (74A,74B) including a second rail that extends from a cold side of the second liner panel (74A,74B) 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 (160,162), wherein each angled end surface (160,162) interfaces with the angled shell interface wherein the first liner panel (72A, 72B) is a forward liner panel (72A, 72B), the first rail is an aft rail, the second liner panel (74A, 74B) is an aft liner panel (74A, 74B) and the second rail is a forward rail; wherein the forward and aft rails (122b, 124a) correspond to the forward and aft edges of the aft and forward liner panels (74A, 74B, 72A, 72B) 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 (68,70) includes a cooling impingement passage at an apex of the angled shell interface. a support shell (68,70) with an angled shell interface; a first liner panel (72A,72B) mounted to the support shell (68,70) via a multiple of studs, the first liner panel (72A,72B) including a first rail that extends from a cold side of the first liner panel (72A,72B) 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 (74A,74B) mounted to the support shell (68,70) via a multiple of studs, the second liner panel (74A,74B) including a second rail that extends from a cold side of the second liner panel (74A,74B) 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 (160,162), wherein each angled end surface (160,162) interfaces with the angled shell interface wherein the first liner panel (72A, 72B) is a forward liner panel (72A, 72B), the first rail is an aft rail, the second liner panel (74A, 74B) is an aft liner panel (74A, 74B) and the second rail is a forward rail; wherein the forward and aft rails (122b, 124a) correspond to the forward and aft edges of the aft and forward liner panels (74A, 74B, 72A, 72B) 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 (68,70) includes a cooling impingement passage at an apex of the angled shell interface.