TRANSITION SYSTEM SIDE SEAL FOR GAS TURBINE ENGINES

A gas turbine engine has a transition duct assembly. Between two adjacent transition ducts (20) there is a transition side groove (23) that is formed by transition side rails (22). In this transition side groove (23) is inserted a side seal (30a-30e) that engages transition side grooves (23) that ar...

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Bibliographische Detailangaben
1. Verfasser:	SCHIAVO, Anthony L
Format:	Patent
Sprache:	eng ; fre
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 has a transition duct assembly. Between two adjacent transition ducts (20) there is a transition side groove (23) that is formed by transition side rails (22). In this transition side groove (23) is inserted a side seal (30a-30e) that engages transition side grooves (23) that are formed in the transition side rails (22). L'invention concerne une turbine à gaz comprenant un ensemble conduit de transition. Une rainure latérale de transition (23), qui est formée par des longerons de transition (22), se trouve entre deux conduits de transition adjacents (20). Un joint latéral (30a-30e), qui vient en prise avec des rainures latérales de transition (23) qui sont formées dans les longerons de transition (22), est inséré dans cette rainure latérale de transition (23).