STATOR VANE SYSTEM USABLE WITHIN A GAS TURBINE ENGINE

A stator assembly (10) usable in a gas turbine engine (12) and configured to restrain inner and outer endwalls (14, 16) to limit deflection and prevent clearance loss relative to adjacent blade rotor disks (18) is disclosed. The stator assembly (10) may be formed from a plurality of stator vanes (20...

Ausführliche Beschreibung

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Bibliographische Detailangaben
1. Verfasser:	GRIFFIN, Elliot
Format:	Patent
Sprache:	eng ; fre ; ger
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 stator assembly (10) usable in a gas turbine engine (12) and configured to restrain inner and outer endwalls (14, 16) to limit deflection and prevent clearance loss relative to adjacent blade rotor disks (18) is disclosed. The stator assembly (10) may be formed from a plurality of stator vanes (20) with inner and outer endwalls (14, 16) that are coupled together with a first radially outer tie bar (22). In at least one embodiment, first and second radially outer tie bars (22, 24) may form first and second stator vane segments (26, 28) that together form the circumferentially extending stator assembly (10). The inner and outer endwalls (14, 16) may be coupled together with one or more circumferentially extending alignment pins (30) that limit deflection. The stator assembly (10) may include one more deformable seals (52) extending radially inward from the inner endwall (14).