VOLUTED HOOK-SHAPED ANGEL-WING FLOW DISCOURAGER

VOLUTED HOOK-SHAPED ANGEL-WING FLOW DISCOURAGER

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

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser: ALVAREZ, Raymond, LOCKYER, John, KIM, Yong
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 rotor and stator assemblies. These disk cavities enable hot gas from the hot gas flow path to ingress between the rotor and stator assemblies with detrimental effects to the durability of the turbine (140). Thus, a flow discourager (300) is disclosed that can be integrated into the platform (220) of a stator assembly (144) that is downstream from a rotor assembly (142). The flow discourager (300) comprises a continuous external surface (330) that defines a recirculation zone (230B) within a disk cavity that is aft to a rotor assembly (142) to circulate the hot gas back out into the hot gas flow path.