Transition system side seal for gas turbine engines

A gas turbine engine has transition ducts. Between two adjacent transition ducts there are transition side grooves that extend in a radial direction. A side seal is radially inserted into the transition side grooves. The side seal resiliently engages the transition side grooves to accommodate a ther...

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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 transition ducts. Between two adjacent transition ducts there are transition side grooves that extend in a radial direction. A side seal is radially inserted into the transition side grooves. The side seal resiliently engages the transition side grooves to accommodate a thermo-mechanical stress that develops between the two adjacent transition ducts.