Vorderkantenhybridhohlräume und Kerne für Schaufeln eines Gasturbinenmotors

Details

Veröffentlichungs-Nr.

EP3399145

Aktenzeichen

EP18159671

Anmeldetag

2. März 2018

Veröffentlichung

25. August 2021

Erteilung

25. August 2021

Rechtsraum

EP

IPC

F01D5/18F01D5/20B22C9/10B22C13/10

Abstract

The present invention is related to an airfoil (200) comprising a leading edge hybrid skin core cavity (202) formed within the airfoil extending from the root (200b) to the tip (200a) along a leading edge (206) of the airfoil (200). The cavity (202) having a hot wall (208) and a cold wall (210) has a variable height-to-width ratio (H/W) in a direction from the tip (200a) with a first hot and cold wall geometric profile (208a, 210a) to the root (200b) having a second hot and cold wall geometric profile (208b, 210b). Thus, the aspect ratio, i.e. heigth-to-width ratio, varies along the airfoil span from a first aspect ratio (H1/W1) to a second, different aspect ratio (H2/W2). This geomtric cavity design significantly improves internal heat transfer characteristics, hence, enabling high internal convective heat transfer coefficients due to high flow per unit area.

Anmelder

Firmen

Raytheon Technologies Corporation
United Technologies Corporation

Land

🇺🇸 USA

Fachgebiete