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Research Papers

Periodical Unsteady Flow Within a Rotor Blade Row of an Axial Compressor—Part I: Flow Field at Midspan

[+] 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), 041004 (Jul 31, 2008) (11 pages) doi:10.1115/1.2812329 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 I of the paper, the flow field at midspan of the rotor blade row will be discussed. Different aspects of the blade row interaction process are considered for the design point and an operating point near the stability limit. The periodical unsteady blade-to-blade velocity field is dominated by the incoming stator wakes, while the potential effect of the stator blades is of minor influence. The inherent vortex structures and the negative jet effect, which is coupled to the wake appearance, are clearly resolved. Furthermore the time-resolved profile pressure distribution of the rotor blades is discussed. Although the negative jet effect within the rotor blade passage is very pronounced, the rotor blade pressure distribution is nearly independent of the convectively propagating chopped stator wakes.

FIGURES IN THIS ARTICLE
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Copyright © 2008 by American Society of Mechanical Engineers
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Figures

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Figure 4

Stepwise moved stator blade rows during LDA measurements (reference rotor-stator position: Δϕ=0)

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Figure 11

Unsteady pressure distribution on PS and SS of Rotor 3, midspan, design point (ξ=1.00, ζ=1.0)

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Figure 12

Unsteady pressure distribution on PS and SS of Rotor 3, midspan, operating point near stability at design speed (ξ=0.85, ζ=1.0)

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Figure 3

LDA measurement grid at midspan (r*=50%)

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Figure 5

Definition of perturbation velocity wp

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Figure 6

Rotor blade equipped with piezoresistive pressure transducers on PS and SS (view on PS)

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Figure 7

Periodical unsteady flow field inside the blade passages of Rotor 3, reference rotor-stator position (Δϕ=0), midspan, design point (ξ=1.0, ζ=1.0)

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Figure 8

Flow field inside a blade passage of Rotor 3, parameters along midpassage, comparison of time-resolved result (Δϕ=0) and time-averaged values, midspan, design point (extracted from Fig. 7)

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Figure 9

Periodical unsteady flow field inside the blade passages of Rotor 3, rotor-stator position Δϕ=0.25, midspan, design point (ξ=1.0, ζ=1.0)

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Figure 10

Periodical unsteady flow field inside the blade passages of Rotor 3, reference rotor-stator position (Δϕ=0), midspan, operating point near stability limit at design speed (ξ=0.85, ζ=1.0)

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Figure 1

(a) Negative jet effect within a compressor blade row; (b) effect of negative jet on velocity and pressure at a fixed position near the blade surface

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Figure 2

Sectional drawing of the Dresden LSRC

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