초록 ▼

A turbomachine has inner and outer annular shells of metal material containing, in a gas flow direction F, a fuel injector assembly, a composite material annular combustion chamber, and an nozzle of metal material forming the fixed-blade inlet stage of a high pressure turbine. Provision is made for

A turbomachine has inner and outer annular shells of metal material containing, in a gas flow direction F, a fuel injector assembly, a composite material annular combustion chamber, and an nozzle of metal material forming the fixed-blade inlet stage of a high pressure turbine. Provision is made for the combustion chamber to be held in position between the inner and outer metal annular shells by a plurality of flexible metal tabs having first ends interconnected by a flange-forming metal ring fixed securely to each of the annular shells by first fixing means, and second ends fixed by second fixing means firstly to the composite material combustion chamber and secondly to one end of a composite material wall whose other end forms a bearing plane for a sealing element secured to the nozzle and providing sealing for the gas stream between the combustion chamber and the nozzle.

대표청구항 ▼

1. A turbomachine comprising a shell of metal material containing in a gas flow direction F: a fuel injector assembly, a composite material combustion chamber having a longitudinal axis, and a metal nozzle forming the fixed blade inlet stage of a high pressure turbine, wherein said composite materia

1. A turbomachine comprising a shell of metal material containing in a gas flow direction F: a fuel injector assembly, a composite material combustion chamber having a longitudinal axis, and a metal nozzle forming the fixed blade inlet stage of a high pressure turbine, wherein said composite material combustion chamber is held in position inside said metal shell by a plurality of flexible metal tabs having first and second ends, said first ends being interconnected by a flange-forming metal ring fixed to said metal shell by first fixing means, and each of said second ends being fixed by second fixing means both to said composite material combustion chamber and to one end of a composite material wall whose other end forms a bearing plane for a sealing element secured to said nozzle and providing sealing for the stream of gas between said combustion chamber and said nozzle, the flexibility of said metal fixing tabs allowing expansion to take place freely in a radial direction at high temperatures between said composite material combustion chamber and said metal shell. 2. A turbomachine according to claim 1, wherein said first and second fixing means are constituted by a plurality of bolts. 3. A turbomachine according to claim 1, wherein said metal shell is made up of two portions, and said metal ring interconnecting said first ends of said flexible metal tabs is mounted between the connection flanges of said two portions. 4. A turbomachine according to claim 1, wherein said metal ring interconnecting said first ends of said flexible metal tabs is fixed directly to said annular shell by conventional fixing means. 5. A turbomachine according to claim 1, wherein said first ends of the flexible metal tabs are fixed by brazing (or welding) to said flange-forming metal ring. 6. A turbomachine according to claim 1, wherein said first ends of the flexible metal tabs are integrally formed with said flange-forming metal ring. 7. A turbomachine according to claim 1, wherein said second fixing means are constituted by crimping elements. 8. A turbomachine according to claim 1, wherein said sealing element is of the circular spring blade gasket type. 9. A turbomachine according to claim 8, wherein said spring blade gasket includes a plurality of calibrated leakage orifices.