| 摘要 |
A securing part structure of a turbine nozzle (11) provided with a plurality of turbine nozzle divided bodies (12) which are each provided with a plurality of stationary blades (6), are disposed annularly around the axis of a jet engine, and secured between a turbine case (2) and a shroud of the jet engine, wherein in the turbine nozzle divided body (12), an arc-shaped outer band (7) which couples respective leading ends of the plurality of stationary blades (6) to each other is provided, and the turbine nozzle divided body (12) is secured between the turbine case (2) and the shroud by engaging an engagement portion (7c) of the outer band (7) with a receiving portion (2a) of the turbine case (2) from behind, fitting a recessed portion (7e) of the outer band (7) to a rotation stopper (9) from behind, and fitting a cutout portion formed in the shroud to a protruding portion (7f) formed at the back side of the recessed portion (7e) from behind. Consequently, a reduction in performance loss and an increase in the life of the turbine case can be achieved. |
