COMBUSTION CHAMBER COMPRISING SECONDARY INJECTION SYSTEMS, AND FUEL SUPPLY METHOD

A combustion chamber for an aircraft turbomachine includes an annular chamber end wall structure, an annular row of main injection systems mounted in the chamber end wall structure and configured to deliver a sheet of fuel, including a central recirculation region and a corner recirculation region a...

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Hauptverfasser: MUSAEFENDIC, Haris, CABRE, Jean-François, LUNEL, Romain Nicolas, LEPAROUX, Julien Marc Matthieu
Format: Patent
Sprache:eng
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Zusammenfassung:A combustion chamber for an aircraft turbomachine includes an annular chamber end wall structure, an annular row of main injection systems mounted in the chamber end wall structure and configured to deliver a sheet of fuel, including a central recirculation region and a corner recirculation region around the central recirculation region, and secondary injection systems each configured to inject an additional flow of air and fuel directly into a corresponding corner recirculation region.