Multi-stage compressor

Research output: Intellectual propertyPatent application/Patent

Contributors

Abstract

A multi-stage compressor, namely a multi-stage radial compressor or a multi-stage diagonal compressor, having a compressor rotor, the compressor rotor has a rotor shaft and multiple impellers fastened to the rotor shaft which are subjected to inflow in the axial direction and impellers which are subjected to outflow in the radial direction or diagonal direction. Each impeller has a curved inner shroud, a curved outer shroud and multiple curved impeller blades arranged between the inner shroud and the outer shroud. The inner shroud, the outer shroud, and the impeller blades each consists of a fibre composite material. The rotor shaft extends through a recess in the inner shroud of the respective impeller.

Details

A multi-stage compressor, namely a multi-stage radial compressor or a multi-stage diagonal compressor, having a compressor rotor, the compressor rotor has a rotor shaft and multiple impellers fastened to the rotor shaft which are subjected to inflow in the axial direction and impellers which are subjected to outflow in the radial direction or diagonal direction. Each impeller has a curved inner shroud, a curved outer shroud and multiple curved impeller blades arranged between the inner shroud and the outer shroud. The inner shroud, the outer shroud, and the impeller blades each consists of a fibre composite material. The rotor shaft extends through a recess in the inner shroud of the respective impeller.
Original languageEnglish
IPC (International Patent Classification)F04D 29/28
Patent numberUS 2025/0361870
Filing date6 May 2025
Country/TerritoryUnited States of America
Priority date23 May 2024
Priority numberDE 102024114446
Publication statusE-pub ahead of print - 27 Nov 2025
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External IDs

ORCID /0000-0003-1370-064X/work/199960721

Keywords