Gasturbinenmotorrotorschaufelübergang

Details

Veröffentlichungs-Nr.

EP4749083

Anmeldetag

20. November 2025

Veröffentlichung

27. Mai 2026

Rechtsraum

EP

IPC

F01D5/14, F01D5/18

Abstract

A rotor blade (58) for a gas turbine engine (20) is provided that includes an airfoil (68), an attachment section (64), and a neck section (66). The airfoil (68) includes a plurality of internal cooling air passages (90). The attachment section (64) has a base surface (70). A forward center cooling air passage (190AF) is open at the base surface (70) and extends through the attachment and neck sections (64). An aft center cooling air passage (190AA) is open at the base surface (70) and extends through the attachment and neck sections (64). A wall to wall, W2W, cooling air passage (190B) is open at the base surface (70) and extends through the attachment and neck sections (64). The W2W cooling air passage (190B) is disposed between the forward and aft center cooling air passages (190AF). In a transition in a direction from a cross-sectional plane disposed in the attachment section (64) to the airfoil root end (84), a side segment (194, 196) progressively extends outwardly from the W2W cooling air passage.

Anmelder

Firma

RTX Corporation

Land

🇺🇸 USA