Patent ID: 8262345

Claim:
A turbine engine, comprising: a high-pressure turbine; a low-pressure turbine; and a transition section disposed between the high-pressure turbine and the low-pressure turbine and configured to direct combustion fluids from the high-pressure turbine to the low-pressure turbine, wherein at least one component of the transition section comprises a ceramic matrix composite; a variable area turbine nozzle annularly disposed within the transition section, wherein the variable area turbine nozzle comprises: a plurality of variable airfoils extending between first inner and outer surfaces, wherein the plurality of variable airfoils and the first inner and outer surfaces are each constructed of the ceramic matrix composite; and a plurality of fixed airfoils extending between second inner and outer surfaces, wherein the plurality of fixed airfoils and the second inner and outer surfaces are each constructed of the ceramic matrix composite; wherein the ceramic matrix composite of the plurality of variable airfoils, the first inner and outer surfaces, the plurality of fixed airfoils, and the second inner and outer surfaces is directly exposed to the combustion fluids.