Komponenten für Gasturbinentriebwerke

Details

Veröffentlichungs-Nr.

EP3748126

Aktenzeichen

EP20178294

Anmeldetag

4. Juni 2020

Veröffentlichung

24. Mai 2023

Erteilung

24. Mai 2023

Rechtsraum

EP

IPC

F01D5/18

Abstract

Component for gas turbine engines (20) are described. The components include an airfoil body (402; 502) having leading and trailing edges (404, 406) and pressure and suction sides (408, 410). The airfoil has a leading edge cavity (412; 512) located proximate the leading edge (404) defined between the leading edge (404) and a separator rib (426; 526) and between the pressure side (408) and the suction side (410). An insert member (418; 518; 618) is installed within the leading edge cavity (412; 512). The insert member (418; 518; 618) has one or more metering flow apertures (420; 520; 620) at an aft end and one or more impingement apertures (422; 522; 622) at a forward end and at least one axially extending rib (530; 630) along an exterior surface thereof. At least one axial extending flow channel passage (532; 632) is defined along the axial extending rib (530; 630) between an exterior of the insert member (418; 518; 618) and an interior of the airfoil body (402; 502). Air flow through the metering flow apertures (420; 520; 620) flows into the axial extending flow channel passage (532; 632) and flows forward toward the leading edge (404).

Anmelder

Firmen

RTX Corporation
Raytheon Technologies Corporation

Land

🇺🇸 USA

Fachgebiete