Verfahren zur Herstellung eines Inspektionszugangsdurchgangs für ein Flugzeugantriebssystem

Details

Veröffentlichungs-Nr.

EP4760053

Anmeldetag

12. Dezember 2025

Veröffentlichung

17. Juni 2026

Rechtsraum

EP

Abstract

A method for forming an access passage (168) for a gas turbine engine (24) of an aircraft propulsion system (22) includes installing a tooling jig (144) on an engine case (70) of the gas turbine engine (24) at a port (88) at a turbine section (34) radially outward of a turbine vane stage (72), aligning the tooling jig (144) on the engine case (70) and fixedly mounting the tooling jig (144) on the engine case (70), and drilling a first access aperture (172) of the access passage (168) through the inner ring (92) along the tooling axis (152) with a drill bit (180) inserted into the first turbine vane through a tooling aperture (150) of the tooling jig (144). The access passage (168) extends through the turbine vane stage (72) to a rotor cavity (86) disposed radially inward of the turbine vane stage (72) and between an upstream rotor stage (66) and a downstream rotor stage (68) of a bladed turbine rotor.

Anmelder

Firma

RTX Corporation

Land

🇺🇸 USA