Topologie und Entstehung von Blattspitzenwirbeln in transsonischen Verdichterrotoren und ihr Einfluss auf die Stabilitätsgrenze

A numerical experiment has been carried out to define the near-stall casing endwall flow field of a transonic compressor rotor. The rotor, known as Rotor 37, is highly loaded and has a relative inlet Mach number that is supersonic at the hub at design flow conditions. The experiment based on flow simulations at different wheel speeds for one blade passage with periodic boundaries incorporating a fully gridded tip gap. The flow calculations are preformed with a commercial simulation code solving the fully three-dimensional Reynolds-averaged Navier-Stokes equations. The results of the simulation show that the interaction of the tip leakage vortex and the passage shock plays a major role in determining the rotor flow range. More specifically, the computations imply that it is the area increase of this vortex as it passes through the passage shock that is the source of the blockage associated with stall.

Grantor dc:publisher

Publikationsserver der RWTH Aachen University

Year dc:date

2006

Author dc:creator

• Hofmann, Willy H.

Contributors dc:contributor

• Ballmann, Josef

• info:eu-repo/classification/ddc/620
• Ingenieurwissenschaften
• Transsonisch
• Axialverdichter
• Stabilitaetsgrenze
• Blattspitzenwirbel
• Stoss-Wirbel Interaktion
• Wirbelaufplatzen
• Transonic
• Axial-Compressor
• Stability Limit
• Tip Vortex
• Shock-Vortex Interaction
• Vortex breakdown

Statement dc:rights

• info:eu-repo/semantics/openAccess

Language dc:language

ger

Identifier

https://publications.rwth-aachen.de/search?p=id:%22RWTH-CONV-114769%22

OAI record oai:identifier

https://publications.rwth-aachen.de/oai2d?verb=GetRecord&metadataPrefix=oai_dc&identifier=oai%3Apublications.rwth-aachen.de%3A52554