Invention Grant
US09279588B2 Combustion chamber of an aeronautical turbine engine with combustion holes having different configurations 有权
具有不同结构的燃烧孔的航空涡轮发动机的燃烧室

Combustion chamber of an aeronautical turbine engine with combustion holes having different configurations
Abstract:
A combustion chamber for an aviation turbine engine, the combustion chamber being annular about a longitudinal axis and including an outer side wall, an inner side wall, and an annular chamber end wall connecting one end of the outer side wall to one end of the inner side wall. The outer side wall includes, distributed along its circumference, spark plugs, primary holes, and dilution holes situated downstream from the primary holes in the direction of the longitudinal axis. The primary holes situated in each of the adjacent zones adjacent to one of the spark plugs present a configuration that is different from the configuration of the primary holes situated outside the zones, such that the supply of air in the adjacent zones is different from the supply of air outside the zones.
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