Combustor shape cooling system
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United States of America Patent
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Aug 20, 2019
Grant Date -
Feb 16, 2017
app pub date -
Aug 10, 2016
filing date -
Aug 13, 2015
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Abstract
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.
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