Patent ID: 7328582
Filing Date: 2008-02-12
Classification: F23R

Abstract:
1. An annular turbine engine combustion chamber, comprising: an external axial wall; an internal axial wall; and a chamber base that links said external and internal axial walls, with the chamber base possessing a series of injection ports and a series of holes with said injection ports configured to at least allow injection of fuel into an interior of the combustion chamber and said holes configured to allow a supply of cooling air to pass for cooling the chamber base, wherein the chamber base is equipped with an external portion in which the holes are made to direct a first part of the supply of cooling air towards the external axial wall and an internal part in which the holes are made to direct a second part of the supply of cooling air towards the internal axial wall, and wherein the chamber is configured so that in an axial half-section, taken in any manner whatsoever between two directly successive injection ports, (1) values of first acute angles formed between a line that is effectively a median of the half-section located between the external axial wall and the internal axial wall and principal directions, in this half-section, of the holes of the external portion, decreases as a function of a distance between the holes and this line that is effectively the median, and (2) values of the second acute angles formed between the line that is effectively the median and the principal directions, in this half-section, of the holes in the internal portion, decrease as a function of the distance between the holes and the line that is effectively the median.