Ring-shaped combustion chamber for a turbine engine
AssigneeSafran Helicopter Engines
InventorsStéphane Pascaud, Guillaume Taliercio
Life of this patent
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Abstract
An annular combustion chamber (10) having a first annular wall (12) and a second annular wall (13) that are coaxial about an axis (X), a chamber end wall (14) connecting together the first and second walls (12, 13), and a plurality of injectors (16), the first wall (12) including first air feed holes (18) downstream from the injectors (16), the combustion chamber (10) being characterized in that for at least a first one of said injectors (16), at least three of the first holes (18) sharing the first injector as their closest injector are situated at equal distances (D) from the first injector (16).
Claims12
An annular combustion chamber having a first annular wall and a second annular wall that are coaxial about an axis, a chamber end wall connecting together the first and second walls, and a plurality of injectors, the first wall including first air feed holes downstream from the injectors, wherein for at least a first one of said injectors, at least three of the first air feed holes sharing the first injector as a closest injector thereto are situated at equal distances from a point on the first injector.
Dependencies are inferred from the claim text.