Turbomachine combustion chamber having a perforated chamber end wall and with no deflector

摘要

An annular combustion chamber for a turbomachine, including an external wall and an internal wall which are oriented substantially axially relative to the rotation axis of the turbomachine, the combustion chamber being closed upstream by a chamber end wall oriented substantially radially, the chamber being supplied with compressed air coming from a compressor via a nozzle, the output direction of which is offset radially relative to the mid-axis of the combustion chamber, the chamber end wall including cooling air supply holes inclined to the direction normal to the chamber end wall. The number of holes oriented radially in the direction opposite to that where the outlet of the nozzle is located is greater than the number of holes oriented radially in the direction of the outlet of the nozzle.

主权项

1. An annular combustion chamber for a turbomachine comprising:
an outer wall and an inner wall which are oriented substantially axially with respect to an axis of rotation of the turbomachine and which is closed at an upstream end by a chamber end wall oriented substantially radially, the annular combustion chamber being supplied with compressed air from a compressor by a diffuser with an outlet having an outlet direction radially offset from a median axis of the annular combustion chamber, the chamber end wall comprising cooling-air supply perforations which are inclined with respect to a direction normal to the chamber end wall, the cooling-air supply perforations being arranged in rows which are circular and concentric with the axis of rotation, wherein the diffuser is radially offset from the median axis in a determined direction, and wherein a density of the cooling-air supply perforations in the chamber end wall increases from a median of the chamber end wall to radially inner and outer peripheries of the chamber end wall in a radial direction, and the density of cooling-air supply perforations at the radially inner periphery of the chamber end wall is greater than the density of cooling-air supply perforations at the radially outer periphery of the chamber end wall.