Kernanordnung für Turbinenmotorkomponente

Details

Veröffentlichungs-Nr.

EP3088100

Aktenzeichen

EP16167665

Anmeldetag

29. April 2016

Veröffentlichung

1. Januar 2020

Erteilung

1. Januar 2020

Rechtsraum

EP

IPC

B22C9/10F01D5/18B22C9/06B22D25/02B22D15/00B22D17/00F01D5/14

Abstract

A casting core (196) for an airfoil (165) includes a first portion (197) extending in a first direction and corresponding to a first cavity (179, 180) of an airfoil (165). The first portion (197) defines a reference plane along a parting line (204) formed by a casting die (202). The first portion (197) defines a plurality of grooves (212) corresponding to a plurality of trip strips (195) of the airfoil (165). Each of the plurality of grooves (212) defines a respective groove axis (214), and the plurality of grooves (212) are distributed in the first direction along a first side of the reference plane such that one or more of the groove axes (214) are oriented with respect to a pull direction (P) of the casting die (202). A method for fabricating a gas turbine engine component is also disclosed.

Anmelder

Firma

United Technologies Corporation

Land

🇺🇸 USA

Fachgebiete