Mounting a turbine nozzle on a combustion chamber having CMC walls in a gas turbine
AssigneeSnecma
InventorsCaroline Aumont, Eric Conete, Mario De Sousa, Didier Hernandez, Georges Habarou
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Abstract
The gas turbine comprises an annular combustion chamber having inner and outer walls made of ceramic matrix composite material, and a high pressure turbine nozzle secured to a downstream end of the combustion chamber and comprising a plurality of stationary airfoils extending between the inner and outer walls of an annular flow path through the nozzle for the gas stream coming from the combustion chamber. The turbine nozzle is made of ceramic matrix composite material and it is connected to the downstream end of the combustion chamber by brazing.
Claims22
A gas turbine comprising an annular combustion chamber with inner and outer walls of ceramic matrix composite material, a high pressure turbine nozzle integral with a downstream end of the combustion chamber and comprising a plurality of stationary airfoils extending between the inner and outer walls of an annular flow path through the nozzle for the gas stream coming from the combustion chamber,
- wherein the turbine nozzle is made of a ceramic matrix composite material and is connected to the downstream end of the combustion chamber by brazing.
Dependencies are inferred from the claim text.