COMBINED TURBINE NOZZLE AND SHROUD DEFLECTION LIMITER

A gas turbine engine annular turbine nozzle assembly includes airfoils extending between inner and outer band segments coaxial and circumscribed about a centerline axis. Shroud segment extends downstream from outer band segment. A middle outer flange may be between the segments and they may be integ...

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Bibliographische Detailangaben
Hauptverfasser:	LENIHAN, MEGHAN MARY, TAGLIERI, MICHAEL EDMUND, MANTEIGA, JOHN ALAN, HOOPER, TYLER FREDERICK
Format:	Patent
Sprache:	eng
Schlagworte:	BLASTING ENGINE PLANTS IN GENERAL HEATING LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES WEAPONS
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Beschreibung
Zusammenfassung:	A gas turbine engine annular turbine nozzle assembly includes airfoils extending between inner and outer band segments coaxial and circumscribed about a centerline axis. Shroud segment extends downstream from outer band segment. A middle outer flange may be between the segments and they may be integral, monolithic, and integrally formed such as by equiax, directionally solidified, or single crystal casting. Outer band segment may extend axially between arcuate forward and middle outer flanges. One or more deflection limiters on outer band segment limit amount of axial excursion at inner band segment. Limiters may include one or more outward projections respectively extending upwardly or radially outwardly from the middle outer flange. An annular outer casing surrounding the assembly includes inwardly extending inward projections at or about at axial and circumferential locations of limiters or outward projections. Assembly may include bonded together singlets.