| 摘要 |
A gas turbine engine includes a combustor which has at least one annular wall (40, 42) defining a combustion chamber (44) therein. The annular wall (40, 42) is formed by a circumferential array of panels (60) overlapping one with another to define a plurality of radial gaps (62) between respective adjacent two panels (60). The radial gaps (62) are configured in a spiral pattern and are in fluid communication with the combustion chamber (44) and a space outside the combustor to allow air surrounding the annular wall (40, 42) to enter the combustion chamber (44) via the radial gaps (62) for film cooling. |
