Turbomachine blade with improved cooling

US12091989B2 · kind B2 · utility

Assignees

• SAFRAN · FR
• SAFRAN AIRCRAFT ENGINES · FR

Inventors

• Léandre Ostino · Moissy-Cramayel, FR
• Pierre Guillaume Auzillon · Moissy-Cramayel, FR
• Michel Slusarz · Moissy-Cramayel, FR
• Patrice Eneau · Moissy-Cramayel, FR
• Thomas Olivier Michel Pierre De Rocquigny · Moissy-Cramayel, FR
• Romain Pierre Cariou · Moissy-Cramayel, FR
• Ba-Phuc Tang · Cergy, FR
• Adrien Bernard Vincent Rollinger · Moissy-Cramayel, FR
• Vianney Simon · Moissy-Cramayel, FR

Key dates

• Filing date: Apr 24, 2020
• Grant date: Sep 17, 2024
• Expiry date: Apr 24, 2040

Classification

• Technology area (CPC Y): Emerging Cross-Sectional Technologies
• CPC primary: Y02T50/60
• WIPO field: Materials, metallurgy
• WIPO sector: Chemistry

Abstract

A turbine vane includes a root carrying a blade terminated by a squealer tip, the blade having intrados and extrados walls, a leading edge, a trailing edge, and a tip wall delimiting a bottom of the squealer tip, by which the intrados wall is connected to the extrados wall. The blade also includes: a serpentine median circuit, including a first radial pipe that collects air at the root and is connected by a first bend to a second radial pipe that is connected by a second bend to a third radial pipe; a cavity under the squealer tip running along the extrados wall and extending from a central region of the squealer tip to the trailing edge; and a central radial pipe collecting air at the root and extending between at least two of the three pipes of the median circuit and directly supplying the cavity under the squealer tip.