Patent ID: 6732532
Filing Date: 2004-05-11
Classification: F05B,F23R

Abstract:
A turbomachine comprising an annular shell 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 an annular nozzle of metal material having fixed blades and forming the inlet stage of a high pressure turbine; wherein said composite material combustion chamber is held in position in said annular metal shell by a plurality of flexible metal tongues regularly distributed around said combustion chamber, each of said tongues comprising three branches connected in a star configuration, the ends of two of the three branches being securely fixed to a downstream end of said composite material combustion chamber remote from said injection system via respective first and second fixing means, while the end of the third branch thereof is securely fixed to said annular metal shell by third fixing means, the flexibility of said fixing tongues making it possible at high temperatures for said composite material combustion chamber to expand freely in a radial direction relative to said annular metal shell.