Method for operating a compressor of a turbomachine comprising providing a plurality of stages in a front compressor area, a rear compressor area, and allowing a swirl in the rear compressor area

US10641288B2 · kind B2 · utility

Assignee

• MTU Aero Engines AG · DE

Inventors

• Tim Schneider · Dachau, DE
• Sergio Elorza Gomez · Munich, DE

Key dates

• Filing date: Nov 22, 2016
• Grant date: May 5, 2020
• Expiry date: Oct 8, 2037

Classification

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

Abstract

Described is a method for operating a compressor of a turbomachine, in which, when considered in the direction of a main flow, an, in particular, radially averaged degree of reaction has dropped in a front compressor area from a maximum to a minimum, is held constant or virtually constant across a central compressor area up into a rear compressor area, an, in particular, radially averaged degree of reaction being adjusted in the rear compressors area which is closer to the minimum than to the maximum, and a residual swirl of at least 47° is present in the middle section, and a compressor and a turbomachine.