Benutzer: Gast  Login
Titel:

Blade design and tip clearance flow analysis for a compact high-pressure compressor rear stage

Dokumenttyp:
Konferenzbeitrag
Autor(en):
Köhler, Christian Peter; Helcig, Christian; Gümmer, Volker
Abstract:
One way to mitigate the environmental impact of an aero-engine is the increase of thermal efficiency by implementing higher core engine pressure ratios. A higher core engine pressure ratio inevitably leads to a reduction of the compressor's cross-sectional area and thus to an increase of the relative rotor tip clearance heights. The large clearances cause detrimental aerodynamic effects, which penalize the compressor's operational behavior. This paper presents the numerical design efforts for a...     »
Horizon 2020:
This paper is based on the fundings within the project "FloCoTec", which has received funding from the Clean Sky 2 Joint Undertaking (JU) under grant agreement No. 821435. The JU receives support from the European Unions (EU) Horizon 2020 research and innovation programme and the Clean Sky 2 JU members other than the Union.
Kongress- / Buchtitel:
14th European Conference on Turbomachinery Fluid Dynamics and Thermodynamics
Verlag / Institution:
European Turbomachinery Society
Jahr:
2021
Reviewed:
ja
Sprache:
en
Volltext / DOI:
doi:10.29008/etc2021-509
 BibTeX