Patent ID: 6708495
Filing Date: 2004-03-23
Classification: F05B,F23R

Abstract:
A turbomachine comprising inner and outer annular shells of metal material containing in a gas flow direction F: a fuel injector assembly, an annular combustion chamber of composite material and having a longitudinal axis, and an annular nozzle of metal material and forming the fixed-blade inlet stage of a high pressure turbine, wherein said composite material combustion chamber is held in position between said inner and outer metal annular shells by a plurality of flexible metal tongues, first ends of said tongues being interconnected by a metal ring fixed securely to each of said inner and outer metal annular shells by first fixing means, and second ends being fixed by second fixing means on a ring of composite material fixed securely to said composite material combustion chamber, the flexibility of said metal fixing tongues allowing expansion to take place freely in a radial direction at high temperatures between said composite material combustion chamber and said metal annular shells.