Gas turbine combustion chamber wall structure for minimizing cooling film disturbances

A wall structure for a combustion chamber of a gas turbine engine comprising:

• a) a plurality of wall segments, each wall segment having an upstream portion and a downstream portion, each downstream portion having an inner surface facing into the combustion chamber and an outer surface facing away from the combustion chamber;
• b) means attaching an upstream portion of one segment to the outer surface of the downstream portion of an adjacent segment along a juncture line so as to define a cooling chamber having an outlet facing generally in a downstream direction to direct cooling air along the inner surface of the downstream portion;
• c) a plurality of main cooling air holes having air inlets defined by the upstream portion and communicating with the cooling chamber the upstream portion being oriented such that at least one of the main cooling air holes has an air inlet substantially co-planar with the juncture line;
• and,
• d) a primary air hole defined by the downstream portion and communicating with the combustion chamber to supply combustion/dilution air to the combustion chamber, and located such that the primary air hole is substantially tangent to the juncture line and is immediately adjacent to the main cooling air holes so as to minimize the disturbances of the cooling air emanating from the cooling chamber and passing along the inner surface of the downstream portion by air passing through the primary air hole.