| 摘要 |
A gas turbine engine combustor is provided, having a single wall sheet metal liner which is generally annular in shape which may be corrugated and a multi-hole film cooling means which includes at least one pattern of a great many small closely spaced sharply downstream angled film cooling holes [80] disposed essentially along portion of the liner to be cooled. Another embodiment provides a corrugated aircraft engine afterburner sheet metal liner having at least one pattern of great many small closely spaced sharply downstream angled film cooling holes disposed essentially along the entire surface of the liner. <IMAGE> <IMAGE> |
