Ceramic matrix composite turbine nozzle, transition duct and turbine engine

摘要

In one embodiment a transition section (16) for a turbine engine (10) is provided that includes one or more components constructed of a ceramic matrix composite. The transition section (16) may fluidly connect a high-pressure turbine (12) and a low-pressure turbine (14) within the gas turbine engine (10). The transition section (16) may include a transition duct (33) and a variable area turbine nozzle (44). One or both of the transition duct (33) and the variable area turbine nozzle (44) may be constructed of the ceramic matrix composite.