COMBUSTOR LINER PANEL END RAILS FORMING AN ANGLED COOLING INTERFACE PASSAGE FOR A GAS TURBINE ENGINE COMBUSTOR

摘要

A combustor for a gas turbine engine includes a support shell (68,70) with an angled shell interface; a first liner panel (72A,B) mounted to the support shell (68,70) via a multiple of studs, the first liner panel (72A,B) including a first rail (124a) that extends from a cold side of the first liner panel (72A,B) adjacent to the angled shell interface; and a second liner panel (74A,B) mounted to the support shell (68,70) via a multiple of studs, the second liner panel (74A,B) including a second rail (122b) that extends from a cold side (110) of the second liner panel (74A,B) adjacent to said first rail (124a), the second rail (122b) adjacent to the angled shell interface (150).