Blade outer air seal for a gas turbine engine and corresponding gas turbine engine

Blade outer air seal for a gas turbine engine and corresponding gas turbine engine

A blade outer air seal (12) for a gas turbine engine includes a body (22) having an outer radial surface (28), an inner radial surface (30), and a plurality of cooling air apertures (62). The body (22) extends between a forward edge (24) and an aft edge (26). The inner radial surface (30) includes a...

Ausführliche Beschreibung

Gespeichert in:
Bibliographische Detailangaben
Hauptverfasser: Lutjen, Paul M, Tholen, Susan M, Knapp, James N
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 blade outer air seal (12) for a gas turbine engine includes a body (22) having an outer radial surface (28), an inner radial surface (30), and a plurality of cooling air apertures (62). The body (22) extends between a forward edge (24) and an aft edge (26). The inner radial surface (30) includes at least one first seal section (34), at least one second seal section (40), and a riser (44) extending radially between the first seal section (34) and the second seal section (40). Each of the plurality of cooling air apertures (62) extends between the outer radial surface (28) and the riser (44), and each cooling air aperture has an exit (73) configured to direct cooling air substantially parallel to the second seal section (40) of the inner radial surface (30).