Patent ID: 7237388

Claim:
A gas turbine comprising: an annular combustion chamber having a wall made of ceramic matrix composite material; a high pressure turbine nozzle having a plurality of stationary vanes distributed around an axis coinciding with the axis of the combustion chamber, the turbine nozzle being mechanically connected to a downstream end portion of the combustion chamber so as to from an assembly together therewith; inner and outer metal shrouds between which the assembly constituted by the combustion chamber and the turbine nozzle is housed; flexible inner and outer connection ferrules connecting the combustion chamber and turbine nozzle assembly respectively to the inner and outer metal shrouds so as to support said assembly between the shrouds; and locking members preventing the turbine nozzle from turning about its own axis relative to at least one of the metal shrouds so as to avoid the forces that are exerted on the turbine nozzle vanes by the flow of gas from the chamber being taken up by the portions of the connection ferrules that extend between the combustion chamber and turbine nozzle assembly and the metal shrouds.