Rotorstufe für ein Gasturbinentriebwerk

Details

Veröffentlichungs-Nr.

EP4772723

Anmeldetag

30. Dezember 2025

Veröffentlichung

8. Juli 2026

Rechtsraum

EP

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 disk (34) has forward and aft axial end surfaces (62, 64), an outer radial surface that extends between the forward and aft axial end surfaces (63, 64), and disk slots (44) configured to receive rotor blade attachment sections (36). In an assembled state, the attachment sections (36) are fully received in the disk slots (44), and adjacent rotor blade platforms (40), and the outer radial surface of the disk (34) form a tab slot (70). In the assembled state, a central segment (46B) of the seal member (46) is engaged with a platform channel (52) disposed at a platform lateral edge surface (40A), and an axial locator tab (46A, 46E) of the seal member (46) is disposed in the at least one tab slot (70).

Anmelder

Firma

Pratt & Whitney Canada Corp.

Land

🇨🇦 Kanada