Gas turbine engine multi-hole film cooled combustor liner and me

Power plants – Reaction motor – Liquid oxidizer

Patent

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Details

60753, F02C 300, F23R 306

Patent

active

051813793

ABSTRACT:
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 disposed essentially along portion of the liner to be cooled. Another embodiment provided 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.

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