Guide vane arrangement for a turbomachine, compressor module, and turbomachine

US12326091B2 · kind B2 · utility

Assignee

• MTU Aero Engines AG · DE

Inventors

• Alexander Halcoussis · Haimhausen, DE
• Harsimar Sahota · Unterschleißheim, DE

Key dates

• Filing date: Jul 29, 2021
• Grant date: Jun 10, 2025
• Expiry date: Jul 29, 2041

Classification

• Technology area (CPC Y): Emerging Cross-Sectional Technologies
• CPC primary: Y02T50/60
• WIPO field: Engines, pumps, turbines
• WIPO sector: Mechanical engineering

Abstract

A guide vane for arrangement in a gas duct of a turbomachine, including a guide vane blade and an outer platform which, relative to a longitudinal axis of the turbomachine, is arranged radially on an outside on the guide vane blade. The outer platform delimits the gas duct with an inner wall surface radially to the outside. The inner wall surface has a curved profile with an inflection point when viewed in an axial section, the inner wall surface having a concave curvature in a first axial section which is upstream from the inflection point with respect to a flow through the gas duct, and a convex curvature in a second axial section which is arranged downstream from the inflection point with respect to the flow through the gas duct.