Gasturbinenmotor mit Bugwellenabschwächung

Details

Veröffentlichungs-Nr.

EP4807138

Anmeldetag

11. März 2026

Veröffentlichung

16. September 2026

Rechtsraum

EP

IPC

F01D5/14, F01D9/04

Abstract

A gas turbine engine (10) includes a turbomachine (16) having a compressor section (21), a combustion section (26), and a turbine section (27). The turbine section (27) includes a band (270, 275, 280, 285) having an upstream end (320) and a downstream end (328). The band (270, 275, 280, 285) extends between the upstream end (320) and the downstream end (328), and the band (270, 275, 280, 285) at least partially defines the working gas flow path (33). A plurality of airfoils (325) extend into the working gas flow path (33) from the band (270, 275, 280, 285). Each airfoil of the plurality of airfoils (325) includes a leading edge (330), a trailing edge (335), a first side (340), and a second side (345) opposite the first side (340). Each of the plurality of airfoils (325) is substantially symmetric across an airfoil centerline (310) extending through a center of each of the plurality of airfoils (325). The band (270, 275, 280, 285) defines a valley portion (355) adjacent the leading edge (330) of each of the plurality of airfoils (325) and a pair of hill portions (350) on opposing sides of the valley portion (355).

Anmelder

Firma

General Electric Company

Land

🇺🇸 USA

Fachgebiete