Combustion chamber for turbine engine e.g. turbo propeller, of airplane, has air passage openings inclined with respect to axis of chimney in axial direction and circumferential direction so as to form local stream of air on specific level

摘要

The chamber has a spark plug (38) carried by an external casing and axially engaged in a chimney (58) carried by a chamber revolution wall (16). The spark plug extends in an annular air flow vein. Air passage openings (56) are oriented toward an internal end of the spark plug and are inclined with respect to an axis (54) of the chimney in axial direction and circumferential direction so as to form a local stream of air on a specific level. An axis of each opening is tangent to a periphery of the internal end of the spark plug.