TURBINE NOZZLE-TO-SHROUD INTERFACE

A turbomachine includes a compressor 12, a combustor 16, and a turbine 18. The turbine includes a nozzle 202, a shroud 206, and an axial cavity defined between the nozzle and the shroud. The nozzle includes an inner platform 208, an outer platform 210 spaced apart from the inner platform along a rad...

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Bibliographische Detailangaben
Hauptverfasser:	VEDHAGIRI, Sivaraman, ROBERTS, Frederic Woodrow
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 turbomachine includes a compressor 12, a combustor 16, and a turbine 18. The turbine includes a nozzle 202, a shroud 206, and an axial cavity defined between the nozzle and the shroud. The nozzle includes an inner platform 208, an outer platform 210 spaced apart from the inner platform along a radial direction, and an airfoil 212 extending therebetween. The outer platform extends axially between a forward sidewall 214 and an aft sidewall 216. The nozzle also includes an aft hook 222 radially outward of the outer platform and axially forward of the aft sidewall of the outer platform. The shroud includes a forward end 226 adjacent to the aft sidewall of the outer platform. A sealing interface is positioned within the cavity, radially outward of the outer platform of the nozzle and axially forward of the aft sidewall of the outer platform of the nozzle.