Konturierte Endwand für ein Gasturbinentriebwerk

Details

Veröffentlichungs-Nr.

EP3690189

Aktenzeichen

EP20155024

Anmeldetag

31. Januar 2020

Veröffentlichung

5. April 2023

Erteilung

5. April 2023

Rechtsraum

EP

IPC

F01D5/14

Abstract

A vane (62) for a gas turbine engine includes first and second endwalls (64, 66) each having a radially facing surface (70, 72) that bounds a gas path (GP), an airfoil section (62A) extending in a radial direction (R) between the first and second endwalls (64, 66), extending in an axial direction (X) between an airfoil leading edge (62TE) and an airfoil trailing edge, and extending in a circumferential direction between pressure and suction sides (62P, 62S). The radially facing surface (70, 72) of each of the first and second endwalls (64, 66) is axially sloped such that the gas path (GP) converges in the axial direction (X) between the airfoil leading and trailing edges (62LE, 62TE). The first endwall (64, 66) has an axisymmetric contour (74) at least partially swept in the circumferential direction from each of the pressure and suction sides (62P, 62S).

Anmelder

Firmen

RTX Corporation
Raytheon Technologies Corporation
United Technologies Corporation

Land

🇺🇸 USA

Fachgebiete