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
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).