Rotorstufe für ein Gasturbinentriebwerk und Rotorscheibe

Details

Veröffentlichungs-Nr.

EP4775801

Anmeldetag

30. Dezember 2025

Veröffentlichung

15. Juli 2026

Rechtsraum

EP

IPC

F01D11/00, F01D5/30

Abstract

A rotor stage (26A) for a gas turbine engine (20) is provided that includes rotor blades (32A, 32B), a disk (34), and a seal member (46). Each rotor blade (32A, 32B) has an airfoil (42), an attachment section (36), a neck section (38), and a platform (40). The disk (34) includes an inter-slot segment (60) disposed between a first and second disk slot (44) that are adjacent one another. The inter-slot segment (60) includes an outer radial surface (76) and a retaining feature (74) that extends radially outwardly from the outer radial surface (76). In the rotor stage assembled state, the attachment section (36) of a first rotor blade (32A) is received in the first disk slot (44), and the attachment section (36) of a second rotor blade (32B) is received in the second disk slot (44). The retaining feature (74) is configured to limit axial travel of the seal member (46) when the rotor stage (26A) is in the assembled state.

Anmelder

Firma

Pratt & Whitney Canada Corp.

Land

🇨🇦 Kanada

Fachgebiete