AIRFOIL WITH RIB COMMUNICATION OPENINGS

An airfoil (62) for a gas turbine engine (20) according to an example of the present disclosure includes a first cavity (72), a second cavity (74), and a rib (84) extending from a suction sidewall (88) to a pressure sidewall (86) and separating the first cavity (72) from the second cavity (74). The...

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Bibliographic Details
Main Author LORICCO, Nicholas M
Format Patent
LanguageEnglish
French
German
Published 10.07.2019
Subjects
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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Summary:An airfoil (62) for a gas turbine engine (20) according to an example of the present disclosure includes a first cavity (72), a second cavity (74), and a rib (84) extending from a suction sidewall (88) to a pressure sidewall (86) and separating the first cavity (72) from the second cavity (74). The rib (84) includes a central portion (90), a first edge portion (92) extending from the pressure sidewall (86) to the central portion (90), and a second edge portion (94) extending from the suction sidewall (88) to the central portion (90). The rib (84) defines one or more communication openings from the first cavity (72) to the second cavity (74) in the first or second edge portion (92,94).
Bibliography:Application Number: EP20190150475