Anordnung von Filmkühlungsbohrungen für Turbostrahltriebwerkskomponenten

Details

Veröffentlichungs-Nr.

EP3470629

Aktenzeichen

EP18200554

Anmeldetag

15. Oktober 2018

Veröffentlichung

28. April 2021

Erteilung

28. April 2021

Rechtsraum

EP

IPC

F01D5/18F01D9/06

Abstract

The present invention relates to components for gas turbine engines (20) comprising an outer hot gas path surface (75) and a cooling passage (72) configured to deliver a cooling airflow (76). The cooling passage includes a passage wall (77) with a plurality of protrusions (80) along said passage wall (77). The component further comprises a plurality of film cooling holes (94) extending from the passage wall (77) to the outer surface (75). The protrusions (80) are arranged in protrusion rows (82) having a streamwise spacing (84) and an off-streamwise spacing (86). Each of the cooling holes (94) is located in a protrusion wake region (104) in a distance (106), preferably between 0 and 1.5 protrusion diameters (108), downstream of one of the plurality of protrusions (80). This location allows to reduce the separation bubble size downstream the protrusions (80), leading to an improved reattachment of the boundary layer.

Anmelder

Firmen

Raytheon Technologies Corporation
United Technologies Corporation

Land

🇺🇸 USA

Fachgebiete