COMBUSTION CHAMBER COMPRISING ADDITIONAL INJECTION DEVICES OPENING UP DIRECTLY INTO CORNER RECIRCULATION ZONES, TURBOMACHINE COMPRISING SUCH A CHAMBER AND FUEL SUPPLY METHOD FOR SUCH A CHAMBER

摘要

A combustion chamber (18) for aircraft turbomachine, comprising an annular chamber end wall (40), an annular row of injection systems (42) mounted in the annular chamber end wall (40), each injection system comprising at least one air inlet swirler (56, 58) and a main fuel injection nozzle (54) configured to output a fuel stream centred on an injection axis (44) and comprising a central recirculation zone (62) and a corner recirculation zone (64) extending as an annulus around the central recirculation zone (62) chamber, and a plurality of additional fuel injection devices (70) mounted in the chamber end wall (40) and configured to inject fuel (71) directly into the corresponding corner recirculation zones (64) produced by the corresponding injection systems (42) at an operating speed less than or equal to the idling speed.

主权项

1. Combustion chamber (18) for an aircraft turbomachine, comprising:
an annular chamber end wall (40) and two coaxial annular walls (32, 34) connected to each other by said annular chamber end wall and centred on a longitudinal axis (28) of the combustion chamber; and an annular row of injection systems (42) mounted in the annular chamber end wall (40), each injection system comprising at least one air inlet swirler (56, 58) and a main fuel injection nozzle (54) configured to output a fuel stream centred on an injection axis (44) and comprising a central recirculation zone (62) and a corner recirculation zone (64) extending as an annulus around the central recirculation zone (62);wherein:
the combustion chamber also comprises a plurality of additional fuel injection devices (70) mounted in the chamber end wall (40) and configured to inject fuel (71) directly into the corresponding corner recirculation zones (64) produced by the injection systems (42); each additional injection device (70) comprises at least one secondary fuel injection nozzle (72) connected to a fuel supply source (74), and installed to pass through the chamber end wall (40) at a spacing from the corresponding injection system (42); and said at least one secondary injection nozzle (72) of each additional injection device (70) is fitted with a valve configured to go into an open state when the fuel pressure corresponds to an operating speed less than or equal to the idle speed, and to go into a closed state when the fuel pressure corresponds to an operating speed greater than the idle speed.