Integral Beschaufelter Rotor, Gasturbinentriebwerk und Verfahren zur Herstellung eines Integral Beschaufelten Rotors

Details

Veröffentlichungs-Nr.

EP3882437

Aktenzeichen

EP21164108

Anmeldetag

22. März 2021

Veröffentlichung

19. Juni 2024

Erteilung

19. Juni 2024

Rechtsraum

EP

IPC

F01D5/20F01D11/12F01D5/34

Abstract

An integrally bladed rotor,(111) including: a plurality of blades (114; 214; 314; 414) integrally formed with a hub (112) as a single component, each of the plurality of blades (114; 214; 314; 414) having a blade body (124; 324; 424) extending from the hub (112) to an opposed blade tip surface (128; 228; 328; 428) along a longitudinal axis, wherein the blade body (124; 324; 424) defines a pressure side (130; 230; 330; 430) and a suction side (132; 232; 332; 432), and wherein the blade body (124; 324; 424) includes a cutting edge (134; 234; 334; 434) defined between the blade tip surface (128; 228; 328; 428) of the blade body (124; 324; 424) and the pressure side (130; 230; 330; 430) of the blade body (124; 324; 424), wherein the cutting edge (134; 234; 334; 434) is configured to abrade a seal section (116) of an engine case (110). A method for manufacturing an integrally bladed rotor (111) includes: forming a plurality of airfoils integrally with a hub (112) to form a single component, each of the plurality of airfoils having an opposed tip surface (128; 228; 328; 428) with respect to the hub (112) extending along a longitudinal axis, wherein each of the plurality of airfoils defines a pressure side (130; 230; 330; 430) and a suction side (132; 232; 332; 432); and forming a cutting edge (134; 234; 334; 434) between the tip surface (128; 228; 328; 428) and the pressure side (130; 230; 330; 430) of each of the plurality of airfoils, wherein the cutting edge (134; 234; 334; 434) is configured to abrade a seal section (116) of an engine case (110).

Anmelder

Firmen

RTX Corporation
Raytheon Technologies Corporation

Land

🇺🇸 USA

Fachgebiete