Uniform wall thickness in a turbine nozzle duct member enables composite material evaluation without machine failure.
A steam turbine intermediate pressure section uses individual nozzle ring assemblies around a drum rotor within a single shell casing.
Segmented insert design eliminates machining during replacement, reducing gas turbine outage time.
An integrated grommet and insert assembly seals the gas turbine vane tip against pressure loss while simplifying mounting complexity.
A frustoconical flange surface redirects radiative heat away from the structural frame.
A turbine movable sleeve adjusts cross-sectional area via pressure differentials, reducing thermal stresses and mechanical wear across varying flow conditions.