Patent ID: 6668559
Filing Date: 2003-12-30
Classification: F05B,F23R,Y02T

Abstract:
A turbomachine comprising inner and outer annular shells of metal material containing, in a gas flow direction F: a fuel injection assembly; an annular combustion chamber of composite material having a longitudinal axis and a plurality of oxidizer feed orifices; and an annular nozzle of metal material having fixed blades and forming the inlet stage of a high pressure turbine, wherein said combustion chamber of composite material is held in position between said inner and outer annular metal shells by a plurality of flexible metal tongues, first ends of said tongues being interconnected by respective metal rings fixed securely to each of said inner and outer annular metal shells by first fixing means, and second ends of said tongues being fixed securely to said composite material combustion chamber via at least a fraction of said oxidizer feed orifices by second fixing means, the flexibility of said fixing tongues serving, at high temperatures, to accommodate free displacement in radial and axial directions between said composite material combustion chamber and said inner and outer annular metal shells.