Turbomachine blade cooling circuit

US10682687B2 · kind B2 · utility

Assignee

• SAFRAN AIRCRAFT ENGINES · FR

Inventors

• Coralie Cinthia Guerard · Moissy-Cramayel, FR
• Vincent Marc Herb · Alfortville, FR
• Jun Ni · Maumee, US
• Joseph Toussaint Tami Lizuzu · Moissy-Cramayel, FR
• Matthieu Jean Luc Vollebregt · Moissy-Cramayel, FR

Key dates

• Filing date: Jun 7, 2017
• Grant date: Jun 16, 2020
• Expiry date: Jun 7, 2037

Classification

• Technology area (CPC F): Mechanical Engineering; Lighting; Heating
• CPC primary: F05D2250/241
• WIPO field: Materials, metallurgy
• WIPO sector: Chemistry

Abstract

The present disclosure is generally directed to a core configured for the manufacturing of a turbine engine blade by lost-wax casting. The core includes a first convex curved outer face and a second concave curved outer face. The first and second faces have a plurality of recesses, each recess including a spherical portion.