Preferential cooling patterns of film cooling holes for combustion chamber wall

摘要

A gas turbine engine combustor is provided with a single wall sheet metal liner having a generally annular shape, which may be corrugated, and contains at least one preferential pattern of multi-hole film cooling holes. The preferential pattern of cooling holes comprises patterns of small closely spaced sharply downstream angled film cooling holes disposed along portions of the liner so as to direct different amounts of film cooling air to different areas of the liner to accommodate differential heating along the liner. One embodiment of the invention includes a plurality of superimposed preferential cooling hole patterns derived from a base pattern wherein each preferential pattern is formed by skipping patterns of cooling holes in the base pattern. IMAGE