Rotorstufe für ein Gasturbinentriebwerk

Details

Veröffentlichungs-Nr.

EP4768695

Anmeldetag

30. Dezember 2025

Veröffentlichung

1. Juli 2026

Rechtsraum

EP

IPC

F01D11/00, F01D5/30

Abstract

A rotor stage (26A) for a gas turbine engine (20) is provided that includes first and second rotor blades (32A, 32B), a disk (34), and a seal member (46). The rotor blades (32A, 32B) each have an airfoil (42), an attachment section (36), a neck section (38), and a platform (40). The platform (40) has platform inner and outer radial surfaces (40C, 40D). The disk (34) has first and second disk slots (44) that are adjacent one another. In an assembled state, the attachment sections (36) are received in the slots (44). In the assembled state, the platforms (40) of the first and second rotor blades (32A, 32B) and an outer radial surface of the disk (34) form at least one slot (68). The seal member (46) includes a central segment (46B) and an axial locator tab (46A, 46E). In the assembled state, the central segment (46B) is disposed for engagement with the first and second rotor blade platforms (40), and the axial locator tab (46A, 46E) is disposed in the slot (68).

Anmelder

Firma

Pratt & Whitney Canada Corp.

Land

🇨🇦 Kanada

Fachgebiete