TURBINE BLADE HAVING AN IMPROVED STRUCTURE

TURBINE BLADE HAVING AN IMPROVED STRUCTURE

An aviation turbine blade (10) includes at least a first lower surface cavity (C2) and a first upper surface cavity (C3), each adjacent to a first through-cavity (C1) and a second through-cavity (C4), the first upper surface cavity (C3) being adjacent to the upper surface wall (24), the first lower...

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser: ROLLINGER, Adrien Bernard Vincent, PAQUIN, Sylvain, CARIOU, Romain Pierre, FLAMME, Thomas Michel
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:An aviation turbine blade (10) includes at least a first lower surface cavity (C2) and a first upper surface cavity (C3), each adjacent to a first through-cavity (C1) and a second through-cavity (C4), the first upper surface cavity (C3) being adjacent to the upper surface wall (24), the first lower surface cavity (C2) being adjacent to the lower surface wall (22), each of the first and second through-cavities (C1, C4) extending from the lower surface wall (22) as far as the upper surface wall (24), the second through-cavity (C4) including a first inner wall (P1) extending from the upper surface wall (24) as far as the first through-cavity (C1), and a second inner wall (P2) extending from the lower surface wall (22) as far as the first through-cavity (C1). The first (P1) and second (P2) inner walls are not connected.