Gekühlte Turbinenkomponente mit Abwechselnd Ausgerichteten Filmkühllochreihen und Herstellungsverfahren

Details

Veröffentlichungs-Nr.

EP3290638

Aktenzeichen

EP17189120

Anmeldetag

1. September 2017

Veröffentlichung

29. April 2020

Erteilung

29. April 2020

Rechtsraum

EP

IPC

F01D5/18

Abstract

A cooled component (62) for a gas turbine engine includes a plurality of internal ribs extending substantially parallel to a longitudinal axis (A) of the gas turbine engine. The internal ribs are disposed within an internal cavity (110) defining cooling air passages within the cooled component (62). A plurality of cooling holes (84, 85) are arranged in rows (80) with axial orientations alternating between a radially outboard bias directing cooling air radially outward and a radially inboard bias directing cooling air radially inward. Each of the cooling holes (84, 85) includes an internal opening in communication with one of the cooling air passages and an external opening open to an outer surface of the cooled component. The external opening of each of the plurality of cooling holes (84, 85) is disposed on a side opposite the internal rib relative to a corresponding internal opening.

Anmelder

Firmen

Raytheon Technologies Corporation
United Technologies Corporation

Land

🇺🇸 USA

Fachgebiete