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.

主权项

1. A gas turbine engine having a gas generation section including a combustor, the combustor comprising at least one annular wall defining a combustion chamber therein, the at least one annular wall formed by a circumferential array of panels in a loadbearing configuration for bearing loads generated by a combustion reaction taking place in the combustion chamber, the panels extending from an upstream end to a downstream end of the at least one annular wall and overlapping one with another to define a plurality of radial gaps between respective adjacent two of the panels, the radial gaps being configured in a spiral pattern and being in fluid communication with the combustion chamber and a space outside the combustor to allow air surrounding the at least one annular wall to enter the combustion chamber via the radial gaps for film cooling a hot side of the at least one annular wall.