GAS TURBINE ENGINE AIRFOIL WITH COOLING PATH

GAS TURBINE ENGINE AIRFOIL WITH COOLING PATH

A gas turbine engine component includes an airfoil (80) that includes a trailing edge feed cavity (102). A baffle (88) is located in the trailing edge feed cavity (102) and includes a plurality of pressure side cooling openings (120) in fluid communication with a corresponding one of a plurality of...

Ausführliche Beschreibung

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Bibliographische Detailangaben
1. Verfasser: LORICCO, Nicholas M
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 gas turbine engine component includes an airfoil (80) that includes a trailing edge feed cavity (102). A baffle (88) is located in the trailing edge feed cavity (102) and includes a plurality of pressure side cooling openings (120) in fluid communication with a corresponding one of a plurality of pressure side cooling passages. A plurality of suction side cooling openings (124) are in fluid communication with a corresponding one of a plurality of suction side cooling passages.