REDIRECTING STATOR FLOW DISCOURAGER

In the turbine (140) of a gas turbine engine (100), disk cavities exist between stator and rotor assemblies. These disk cavities enable hot gas from the hot gas flow path to ingress between the stator and rotor assemblies with detrimental effects to the durability of the turbine (140). Thus, a flow...

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Bibliographische Detailangaben
Hauptverfasser:	Kim, Yong, Lockyer, John
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:	In the turbine (140) of a gas turbine engine (100), disk cavities exist between stator and rotor assemblies. These disk cavities enable hot gas from the hot gas flow path to ingress between the stator and rotor assemblies with detrimental effects to the durability of the turbine (140). Thus, a flow discourager (300) is disclosed that can be mounted to the stator assembly (144). The flow discourager (300) comprises a continuous external surface (330) that defines a recirculation zone (230B) within the disk cavities to circulate the hot gas back out into the hot gas flow path.