Wall for a turbomachine combustion chamber including an optimised arrangement of air inlet apertures

Abstract

A rotationally symmetrical wall for an aircraft turbomachine combustion chamber, including primary holes, dilution holes positioned downstream from the primary holes, and a plug installation aperture upstream from the primary holes, wherein each first primary hole, considered as one moves away circumferentially from the median axial plane (D) in either direction is positioned at a circumferential position between the circumferential positions of the first dilution hole and of the second dilution hole considered as one moves away circumferentially from the median axial plane (D), wherein the other primary holes are distributed equidistantly, at a predefined interval P, and the distance between the two primary holes is greater than the interval P separating two of the other adjacent primary holes.

1 . A revolution wall for an aircraft turbomachine combustion chamber, comprising:
 a circumferential row of primary holes,   a circumferential row of dilution holes arranged downstream from the primary holes, and   at least one ignition plug installation aperture positioned axially upstream from the primary holes,   wherein the primary holes and the dilution holes are distributed symmetrically either side of a median axial plane of the installation aperture, and   wherein each first primary hole, considered as one moves away circumferentially from the median axial plane in either direction is positioned at a circumferential position between the circumferential positions of the first dilution hole and of the second dilution hole considered as one moves away circumferentially from the median axial plane,   wherein other primary holes are distributed equidistantly, at an interval, and a distance between two primary holes is greater than the interval separating two adjacent primary holes.   
     
     
         2 . A revolution wall according to  claim 1 , wherein each of the other primary holes is positioned at the same circumferential position as an associated dilution hole. 
     
     
         3 . A revolution wall according to  claim 1 , wherein the distance between the first primary hole and the second primary hole found as one moves away circumferentially from the median axial plane is less than the interval separating two of said other adjacent primary holes. 
     
     
         4 . A revolution wall according to  claim 1 , wherein the dilution holes are distributed equidistantly, at an interval roughly equal to half said predefined interval. 
     
     
         5 . A revolution wall according to  claim 1 , further comprising multiperforation holes located between the ignition plug installation aperture and each of said first primary holes. 
     
     
         6 . An annular combustion chamber for an aircraft turbomachine, including a back-of-chamber annular wall and two coaxial revolution walls, which are respectively internal and external, connected to said back-of-chamber wall, and one of which at least is a revolution wall according to  claim 1 . 
     
     
         7 . A turbomachine for aircraft including an annular combustion chamber according to  claim 6 .