Guide vane airfoil for the hot gas flow path of a turbomachine

US11220911B2 · kind B2 · utility

Assignee

• MTU Aero Engines AG · DE

Inventors

• Bernd Kislinger · Reisgang, DE
• Markus Brettschneider · Karlsfeld, DE
• Detlef Korte · Munich, DE
• Bjoern Grueber · Eichenau, DE

Key dates

• Filing date: Feb 18, 2019
• Grant date: Jan 11, 2022
• Expiry date: Feb 22, 2039

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 airfoil for placement in a flow path portion of a turbomachine is provided, which, relative to a flow pattern in flow path portion, has a leading edge and, downstream thereof, a trailing edge, as well as a suction side and a pressure side; relative to a longitudinal axis of the turbomachine, viewed in the axial direction, in a radially inner portion, forming a first angle α with a circular arc about the longitudinal axis, and, in a radially outer portion, a second angle γ with a circular arc about the longitudinal axis. The guide vane airfoil is inclined in the outer portion, thus γ−90°, in terms of absolute value, being >0° (|γ−90°|>0°), and the guide vane airfoil being more highly inclined in the outer portion than in the inner portion, thus γ−90°, in terms of absolute value, being >α−90° (|γ−90°|>α−90°).