An axial-flow turbine (10) according to an embodiment includes a plurality of nozzle structures (20) and a plurality of blade structures (40). At least one nozzle structure includes an outer ring diaphragm (21) and an inner ring diaphragm (22). The outer r...

Thermal control is provided for a gas turbine (110) casing by supplying thermal control gas from a compressor (112) to a space between an outer casing (123) and an inner casing (121), and transferring the thermal control gas from the space through the open...

The present disclosure relates to a gas turbine engine and to a method of controlling a net thrust load on a thrust bearing. The gas turbine engine (20) includes a first non-contacting dynamic rotor seal (84A, 84B, 84C) interfaced with a spool (32), the fi...

A seal mechanism is provided which comprises a structure capable of accommodating radial expansions of turbine rotor without increasing an axial size thereof and providing a reliable sealing property for the turbine rotor for a long time. The seal mechanis...

The device has clamps (25, 26), where one clamp provides sufficient weight to harmonize a dilatation speed of a stator component (22) of a labyrinth seal with respect to that of a rotor unit (28) during acceleration phases of a gas turbine engine. Ventilat...