TURBOMACHINE VANE PROVIDED WITH A COOLING CIRCUIT AND METHOD FOR LOST-WAX MANUFACTURING OF SUCH A VANE

TURBOMACHINE VANE PROVIDED WITH A COOLING CIRCUIT AND METHOD FOR LOST-WAX MANUFACTURING OF SUCH A VANE

A vane (20) for an aircraft turbomachine, said vane comprising a blade (21) and a cooling circuit (28) inside the blade, said cooling circuit (28) comprising at least one longitudinal flow cavity (58) of a cooling air stream (RF), the cooling circuit further comprising elements which protrude into t...

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser: ROLLINGER, Adrien Bernard Vincent, PAQUIN, Sylvain, CARIOU, Romain Pierre, PAGNONI, Filippo
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 vane (20) for an aircraft turbomachine, said vane comprising a blade (21) and a cooling circuit (28) inside the blade, said cooling circuit (28) comprising at least one longitudinal flow cavity (58) of a cooling air stream (RF), the cooling circuit further comprising elements which protrude into the cavity and which are configured to disrupt the air stream, characterised in that each of the protruding elements is generally arc-shaped (50) and internally defines, with a first wall (56), a first cross-sectional flow area (S1-S1', and externally, with a second wall (60) opposite the first wall (56), a second cross-sectional flow area (S2-S2') and each of the elements being configured such that the first or second cross-sectional flow area is reduced from upstream to downstream relative to the direction of the air stream.