direkt zum Inhalt springen

direkt zum Hauptnavigationsmenü

Sie sind hier

TU Berlin

Inhalt des Dokuments

Publikationen am Fachgebiet Luftfahrtantriebe

Physics of Prestall Propagating Disturbances in Axial Compressors and Their Potential as a Stall Warning Indicator
Zitatschlüssel 2017_eck_japplsci
Autor Eck, M. and Geist, S. and Peitsch, D.
Seiten 285
Jahr 2017
ISSN 2076-3417
DOI 10.3390/app7030285
Ort Basel, Switzerland
Journal Journal of Applied Sciences
Jahrgang 7
Nummer 3
Monat 03
Notiz Technische Universität Berlin:
M. Eck, D. Peitsch
Helmut Schmidt Universität, Hamburg:
S. Geist
Verlag MDPI
Wie herausgegeben Creative Commons Attribution 4.0 International License CC-BY 4.0
Zusammenfassung Axial compressors in aero engines are prone to suffering a breakdown of orderly flow when operating at the peak of the pressure rise characteristic. The damaging potential of separated flows is why a safe distance has to be left between every possible operating point and an operating point at which stall occurs. During earlier investigations of stall inception mechanisms, a new type of prestall instability has been found. In this study, it could be demonstrated that the prestall instability characterised by discrete flow disturbances can be clearly assigned to the subject of “Rotating Instabilities”. Propagating disturbances are responsible for the rise in blade passing irregularity. If the mass flow is reduced successively, the level of irregularity increases until the prestall condition devolves into rotating stall. The primary objective of the current work is to highlight the basic physics behind these prestall disturbances by complementary experimental and numerical investigations. Before reaching the peak of the pressure rise characteristic flow, disturbances appear as small vortex tubes with one end attached to the casing and the other attached to the suction surface of the rotor blade. These vortex structures arise when the entire tip region is affected by blockage and at the same time the critical rotor incidence is not exceeded in this flow regime. Furthermore, a new stall indicator was developed by applying statistical methods to the unsteady pressure signal measured over the rotor blade tips, thus granting a better control of the safety margin.
Link zur Publikation [1] Link zur Originalpublikation [2] Download Bibtex Eintrag [3]

Nach oben

------ Links: ------

Zusatzinformationen / Extras

Direktzugang

Schnellnavigation zur Seite über Nummerneingabe

Diese Seite verwendet Matomo für anonymisierte Webanalysen. Mehr Informationen und Opt-Out-Möglichkeiten unter Datenschutz.
Copyright TU Berlin 2008