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TECHNICAL PAPERS

The Effect of Inlet Guide Vanes Wake Impingement on the Flow Structure and Turbulence Around a Rotor Blade

[+] Author and Article Information
Francesco Soranna, Yi-Chih Chow, Oguz Uzol, Joseph Katz

Department of Mechanical Engineering, Johns Hopkins University, Baltimore, MD 21218

J. Turbomach 128(1), 82-95 (Feb 01, 2005) (14 pages) doi:10.1115/1.2098755 History: Received October 01, 2004; Revised February 01, 2005

The flow structure and turbulence around the leading and trailing edges of a rotor blade operating downstream of a row of inlet guide vanes (IGV) are investigated experimentally. Particle image velocimetry (PIV) measurements are performed in a refractive index matched facility that provides unobstructed view of the entire flow field. Data obtained at several rotor blade phases focus on modification to the flow structure and turbulence in the IGV wake as it propagates along the blade. The phase-averaged velocity distributions demonstrate that wake impingement significantly modifies the wall-parallel velocity component and its gradients along the blade. Due to spatially non-uniform velocity distribution, especially on the suction side, the wake deforms while propagating along the blade, expanding near the leading edge and shrinking near the trailing edge. While being exposed to the nonuniform strain field within the rotor passage, the turbulence within the IGV wake becomes spatially nonuniform and highly anisotropic. Several mechanisms, which are consistent with rapid distortion theory (RDT) and distribution of turbulence production rate, contribute to the observed trends. For example, streamwise (in rotor frame reference) diffusion in the aft part of the rotor passage enhances the streamwise fluctuations. Compression also enhances the turbulence production very near the leading edge. However, along the suction side, rapid changes to the direction of compression and extension cause negative production. The so-called wall blockage effect reduces the wall-normal component.

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Copyright © 2006 by American Society of Mechanical Engineers
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Figures

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Figure 5

Streamwise variation of ∂us¯∕∂s along the rotor blade (a) suction side and (b) pressure side, 1.5% chord-lengths away from the surface

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Figure 6

Representation of the process of extension and compression of the IGV wake as it sweeps the rotor blade

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Figure 7

Distribution of normalized ω¯ for different phases. Top row: phases 1 to 3 (leading edge region). Bottom row: phases 4 to 6 (trailing edge region). Contour increment is 0.2.

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Figure 8

Distribution of normalized us′2¯ for different phases. Top row: phases 1 to 3 (leading edge region). Bottom row: phases 4 to 6 (trailing edge region).

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Figure 9

Distribution of normalized vn′2¯ for different phases. Top row: phases 1 to 3 (leading edge region). Bottom row: phases 4 to 6 (trailing edge region).

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Figure 10

Representation of the orientation of the principal strain in different regions around the leading edge and within the rotor passage

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Figure 11

Compressive and extensive principal strain rates distributions in phase 3. The lines indicate the principal directions of compression and extension.

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Figure 12

Distribution of Reynolds stresses locally aligned with the principal directions of compression and extension. The lines indicate the principal directions of compression and extension.

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Figure 13

Streamwise distribution of ∇Se¯∕(10Ω), ◆ (uc′2¯∕Utip2)×103, ◻ (ue′2¯∕Utip2)×103, -- P2D×103∕(Utip3∕c). Distance from suction surface in chord lengths: (a) 3% ; (b) 6%. Phase 3.

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Figure 3

Streamwise variation of the phase-averaged relative lateral velocity (top row) and axial velocity (bottom row) along the rotor blade (a) suction side and (b) pressure side, 1.5% chord-lengths away from the surface

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Figure 4

Streamwise variation of us¯ along the rotor blade (a) suction side and (b) pressure side, 1.5% chord-lengths away from the surface

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Figure 1

(a) The axial turbomachinery test section. (b) Schematic representation of IGV blade and rotor blade. Also indicated: rotor frame coordinates systems (x,y) and (s,n); flow direction and rotor blade displacement direction; area covered by phases 1–6.

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Figure 2

Phase-averaged (a) axial (−u¯), (b) relative lateral (−vr¯) velocity components, and (c) turbulent kinetic energy for three different phases, around the rotor blade leading edge at mid-span. Top row: phase 1 (t∕TS=0.0); middle row: phase 2 (t∕TS=0.213); bottom row: phase 3 (t∕TS=0.426). TS=7.06ms is the stator blade passing period. c=50mm is the rotor blade chord (solid white line). Utip=8m∕s. Contour increments Δu¯=Δvr¯=0.02 and Δk=0.2.

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