Blade channel, blade cascade and turbomachine

US10458248B2 · kind B2 · utility

Assignee

• MTU Aero Engines AG · DE

Inventors

• Nina Wolfrum · Straubing, DE
• Markus Brettschneider · Karlsfeld, DE
• Inga Mahle · Munich, DE
• Markus Schlemmer · Mainburg, DE
• Martin Pernleitner · Dachau, DE

Key dates

• Filing date: Nov 30, 2016
• Grant date: Oct 29, 2019
• Expiry date: Aug 17, 2037

Classification

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

Abstract

A blade channel of a turbomachine that is delimited in the circumferential direction of the turbomachine by a pressure side of an airfoil and by an opposite suction side of an adjacent airfoil that, in the radial direction of the turbomachine, is delimited by two opposing side walls, and whose extent in the axial direction of the turbomachine is delimited by leading edges and by trailing edges of airfoils; at least one of the side walls being provided with localized contours, of which at least two are formed as elevations and at least two as depressions; a saddle surface being formed between the contours that, in one rotation, alternately merges into an elevation and a depression; a blade cascade having such blade channels, as well as a turbomachine having such a blade cascade.