Rotorstufe für ein Gasturbinentriebwerk und Rotorschaufel

Details

Veröffentlichungs-Nr.

EP4772724

Anmeldetag

30. Dezember 2025

Veröffentlichung

8. 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) extends laterally outward from the neck section (38). The platform (40) has platform inner and outer radial surfaces (40C, 40D). The disk (34) has forward and aft axial end surfaces (62, 64) and disk slots (44). A first rotor blade (32A) includes a first rib (72) extending outwardly from a platform inner radial surface (40C). In the assembled state, the blade attachment sections (36) are received in the disk slots (44). In the assembled state, the rotor blade platforms (40) and an outer radial surface of the disk (34) form a tab slot (70). In the assembled state, the first rib (72) locates the seal member (46) relative to platform lateral edge surfaces (40A, 40B).

Anmelder

Firma

Pratt & Whitney Canada Corp.

Land

🇨🇦 Kanada

Fachgebiete