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Experimental investigation of the transonic flow around the leading edge of an eroded fan airfoil

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Abstract

The influence of leading edge modification on the time-averaged and instantaneous flow around a fan airfoil is investigated by particle image velocimetry (PIV), schlieren imaging and high-speed shock shadowgraphs in a transonic cascade windtunnel. In addition to a global characterization of the time-averaged flow using PIV, the instantaneous passage shock position was extracted from single-shot PIV measurements by matching the tracer velocity across the normal shock with an exponential fit. The instantaneous shock positions are assigned to a probability density distribution in order to obtain the average position and the range of fluctuations of the eroded and reference leading edge. The profiles are used to estimate the response time of the particles to the normal shock which was found to be in the sub-microsecond range. Averaged PIV measurements and the probability density of shock position from both geometries are obtained at near stall and choked conditions. In order to extract the frequency range of the shock motion, the shadow of the shock wave was tracked using high-speed shadowgraphy. The paper also provides details on the experimental implementation such as a specifically designed light-sheet probe.

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Abbreviations

\(c\) :

Chord length

\(d\) :

Diameter

\(f\) :

Focal length

\(f_\#\) :

\(f\)-Number, lens aperture

\(M\) :

Mach number

\(m\) :

Magnification

\(p\) :

Blade pitch

\(u\) :

Velocity magnitude

\(\beta\) :

Incidence angle

\(\tau\) :

Particle relaxation time

\(\xi\) :

Particle relaxation length

1:

At cascade entry

0,1:

Upstream and downstream of the shock

n :

Normal to shock

s :

Stagger parameter

p :

Particle parameter

ADP:

Aerodynamic design point (near choking)

AVDR:

Air velocity density ratio

BLE:

Blunt leading edge

DFT:

Discrete Fourier transformation

ODP:

Off design point (near stall)

RANS:

Reynolds-averaged Navier–Stokes

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Acknowledgments

The authors would like to thank Manfred Beversdorff, Wolfgang Steinert and Sebastian Grund for the support during the PIV and high-speed shadowgraph campaigns. Part of the work reported in this paper is performed under the German Aviation Research Program (LuFo IV) funded in part by the Federal Ministry of Economics and Technology. In this context, Lufthansa Technik AG is acknowledged for the good cooperation. Additional funding is provided by the EU-project AFDAR (Advanced Flow Diagnostics for Aeronautical Research, project No. 265695) of the 7th Framework Program whose support is gratefully acknowledged. Finally, the authors would like to thank ANSYS for providing the geometry of the reference blade.

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Authors and Affiliations

  1. Institute of Propulsion Technology, Measurement Technology, German Aerospace Center (DLR), Linder Hoehe, 51147, Cologne, Germany

    Joachim Klinner & Christian Willert

  2. Institute of Propulsion Technology, Fan and Compressor, German Aerospace Center (DLR), Cologne, Germany

    Alexander Hergt

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  1. Joachim Klinner
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  2. Alexander Hergt
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  3. Christian Willert
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Correspondence to Joachim Klinner.

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Klinner, J., Hergt, A. & Willert, C. Experimental investigation of the transonic flow around the leading edge of an eroded fan airfoil. Exp Fluids 55, 1800 (2014). https://doi.org/10.1007/s00348-014-1800-y

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  • DOI: https://doi.org/10.1007/s00348-014-1800-y

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