Patent ID: 8171736
Filing Date: 2012-05-08
Classification: F23R

Abstract:
1. A gas turbine engine combustor comprising an annular combustor shell having a single wall inner liner and a single wall outer liner defining therebetween an annular combustion chamber, the inner and outer liners being discrete and respectively having inner and outer flanges at least partly overlapping to form a dome end portion of the combustor shell, said inner and outer flanges being physically fastened together such as to fix said inner liner and said outer liner in position relative to each other at said dome end portion, at least the outer flange including intersecting first and second wall portions defining a first corner therebetween, the first wall portion being located upstream of the second wall portion and the second wall portion being connected to a remainder of the outer liner through a second corner, the first wall portion extending at least substantially radially inwardly from the first corner and overlapping the inner flange, the second wall portion being frustoconical, the first wall portion having a plurality of cooling apertures defined therethrough immediately upstream of the first corner, the cooling apertures being oriented to direct a cooling air flow from outside the combustor shell therethrough at an angle such that the airflow is injected from the first wall portion following a direction having a radially outward component and along an inner surface of the second wall portion.