COMBUSTOR SHAPE COOLING SYSTEM

摘要

A gas turbine engine includes a combustor which has at least one annular wall defining a combustion chamber therein. The annular wall is formed by a circumferential array of panels overlapping one with another to define a plurality of radial gaps between respective adjacent two panels. The radial gaps are configured in a spiral pattern and are in fluid communication with the combustion chamber and a space outside the combustor to allow air surrounding the annular wall to enter the combustion chamber via the radial gaps for film cooling.