Combustion chamber for gas turbine engine - uses air streams ensuring stoichiometric mixture for all turbine speeds

Abstract

Abstract The combustion chamber for gas turbine engine has combustion zones with holes for radial entry of air streams. Anther air stream enters a mixing or dilution zone. The fuel is atomised by compressed air or by evaporation and enters while entrained in a third air stream. Combustion is ensured at low turbine speeds. Primary air in the second stream is fed independently of the turbine speed and the combustion chamber is hence suited for all turbine speeds. Between fuel injection nozzles and combustion chamber floor (9, 10) is a contracted section 15) upstream of the primary zone. This contraction expands in flow direction of gases and its wall has performations (16) for inlet of air jets from fourth air stream.

Inventors

• 👤 Jean Robert Bedue
• 👤 Jacques Emile Jules Caruel
• 👤 Bruno Deroide
• 👤 Jean-Paul Rene Gaillac
• 👤 Philippe Marc Denis Gastebois

Bibliographic Details