0
Research Papers

Periodical Unsteady Flow Within a Rotor Blade Row of an Axial Compressor—Part II: Wake-Tip Clearance Vortex Interaction

[+] Author and Article Information
Ronald Mailach

 Technische Universität Dresden, Institut für Strömungsmechanik, 01062 Dresden, Germanyronald.mailach@tu-dresden.de

Ingolf Lehmann

 Kompressorenbau Bannewitz GmbH, Windbergstrasse 45, 01728 Bannewitz, Germanyingolf.lehmann@kbb-turbo.de

Konrad Vogeler

 Technische Universität Dresden, Institut für Strömungsmechanik, 01062 Dresden, Germanykonrad.vogeler@tu-dresden.de

J. Turbomach 130(4), 041005 (Jul 31, 2008) (10 pages) doi:10.1115/1.2812330 History: Received June 05, 2007; Revised September 10, 2007; Published July 31, 2008

In this two-part paper, results of the periodical unsteady flow field within the third rotor blade row of the four-stage Dresden low-speed research compressor are presented. The main part of the experimental investigations was performed using laser Doppler anemometry. Results of the flow field at several spanwise positions between midspan and rotor blade tip will be discussed. In addition, time-resolving pressure sensors at midspan of the rotor blades provide information about the unsteady profile pressure distribution. In Part II of the paper, the flow field in the rotor blade tip region will be discussed. The experimental results reveal a strong periodical interaction of the incoming stator wakes and the rotor blade tip clearance vortices. Consequently, in the rotor frame of reference, the tip clearance vortices are periodical with the stator blade passing frequency. Due to the wakes, the tip clearance vortices are separated into different segments. Along the mean vortex trajectory, these parts can be characterized by alternating patches of higher and lower velocities and flow turning or subsequent counter-rotating vortex pairs. These flow patterns move downstream along the tip clearance vortex path in time. As a result of the wake influence, the orientation and extension of the tip clearance vortices as well as the flow blockage periodically vary in time.

FIGURES IN THIS ARTICLE
<>
Copyright © 2008 by American Society of Mechanical Engineers
Your Session has timed out. Please sign back in to continue.

References

Figures

Grahic Jump Location
Figure 4

Periodical unsteady flow field inside the blade passages of Rotor 3 (Δϕ=0), near blade tip (r*=97.9%), design point

Grahic Jump Location
Figure 5

Axial velocity and fluctuations along the tip clearance vortex path of Rotor 3 (Δϕ=0), near blade tip (r*=97.9%), design point

Grahic Jump Location
Figure 6

Periodical unsteady flow field inside the blade passages of Rotor 3 (Δϕ=0): vorticity contours and perturbation velocity vectors, near blade tip (r*=97.9%), design point

Grahic Jump Location
Figure 7

Schematic of tip clearance vortex influenced by the passing wakes, 2D view, near rotor blade tip (r=const, t=const)

Grahic Jump Location
Figure 8

Sequence of periodical unsteady flow field, Rotor 3, near blade tip (r*=97.9%), design point

Grahic Jump Location
Figure 9

Periodical unsteady flow field inside the blade passages of Rotor 3 (Δϕ=0), near blade tip (r*=97.9%), operating point near stability limit at design speed (ξ=0.85, ζ=1.0)

Grahic Jump Location
Figure 10

Time-averaged flow field inside the blade passages of Rotor 3, r*=91.7%, design point

Grahic Jump Location
Figure 11

Periodical unsteady flow field inside the blade passages of Rotor 3 (Δϕ=0), r*=91.7%, design point

Grahic Jump Location
Figure 12

Sequence of periodical unsteady flow field just behind Rotor 3 (z=0.544), design point (ξ=1.0, ζ=1.0)

Grahic Jump Location
Figure 13

Three-dimensional view of the flow field within the rotor blade row (t=const), design point

Grahic Jump Location
Figure 14

Schematic of tip clearance vortex influenced by the passing wakes, 3D view (t=const)

Grahic Jump Location
Figure 1

Schematic of the rotor blade tip clearance flow for steady flow conditions

Grahic Jump Location
Figure 2

Time-averaged flow field inside the blade passages of Rotor 3, near blade tip (r*=97.9%), design point (ξ=1.0, ζ=1.0), dashed line: estimated trajectory of TCV

Grahic Jump Location
Figure 3

Periodical unsteady flow field inside the blade passages of Rotor 3, reference rotor-stator position (Δϕ=0), near blade tip (r*=97.9%), design point (ξ=1.0, ζ=1.0)

Tables

Errata

Discussions

Related

Some tools below are only available to our subscribers or users with an online account.

Related Content

Customize your page view by dragging and repositioning the boxes below.

Related Journal Articles
Related eBook Content
Topic Collections

Sorry! You do not have access to this content. For assistance or to subscribe, please contact us:

  • TELEPHONE: 1-800-843-2763 (Toll-free in the USA)
  • EMAIL: asmedigitalcollection@asme.org
Sign In