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Numerical and experimental investigation of an impeller tip clearance variation in an aero-engine centrifugal compressor with close-coupled pipe-diffuser

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Abstract

The subject of this paper is the experimental and numerical investigation of the influence of impeller tip clearance on the aerodynamics of a high-pressure transonic centrifugal compressor used in an aero-engine application. The overall change in aerodynamic performance of the stage, the isolated impeller and the isolated diffuser is analyzed. Local flow phenomena, responsible for the change in performance, are examined in closer detail. Experimental data from a state-of-the-art test rig, containing detailed 2D particle-image-velocimetry measurements, are used. 3D Reynolds-averaged Navier–Stokes simulations are conducted with the CFD solver turbo-machinery research aerodynamics computational environment to get a detailed insight into the flow field. This study contributes towards a better understanding of the principal flow phenomena of a centrifugal compressor with a close-coupled pipe-diffuser and the additional losses introduced in the individual compressor components by an increased impeller tip clearance.

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Abbreviations

b (mm):

Blade height—hub to tip

c p :

Static pressure recovery

MFC (kg/s):

Corrected mass flow

NML:

Normalized meridional length

NOM:

Nominal tip clearance

OP:

Operation point

PIV:

Particle-image-velocimetry

PS:

Pressure side

RANS:

Reynolds-averaged Navier–Stokes

s [J/(kg K)]:

Entropy

SS:

Suction side

t (mm):

Tip clearance

TC:

Maximum tip clearance

TTR:

Total temperature ratio

TPR:

Total pressure ratio

RPM (1/min):

Revolutions per minute

v (m/s):

Absolute velocity

w (m/s):

Relative velocity

α (°):

Absolute flow angle

η :

Efficiency

λ 2 :

Relative tip clearance = t/b

ξ :

Diffuser center line coordinate

ω :

Total pressure loss

Ω:

Impeller rotation

is:

Isentropic

m:

Meridional

norm:

Normalized value

θ :

Circumferential

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Acknowledgments

General Electric Aviation (GEA) funds the Centrifugal Compressor Technology Project at the Institute of Jet Propulsion and Turbomachinery. This is gratefully acknowledged. Further the GEA Compressor and Fan Aero group (Lynn) extensively supports this research. Special thanks go to the DLR Cologne for the close cooperation and support regarding TRACE.

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Authors and Affiliations

  1. Institute of Jet Propulsion and Turbomachinery, RWTH Aachen, Templergraben 55, 52062, Aachen, Germany

    Benjamin Wilkosz, Robert Kunte, Philipp Schwarz & Peter Jeschke

  2. GE Aviation, 1000 Western Ave MD47410, Lynn, MA, 01910, USA

    Caitlin Smythe

Authors
  1. Benjamin Wilkosz
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  2. Robert Kunte
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  3. Philipp Schwarz
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  4. Peter Jeschke
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  5. Caitlin Smythe
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Corresponding author

Correspondence to Benjamin Wilkosz.

Additional information

This paper is based on a presentation at the German Aerospace Congress, September 10–12, 2012, Berlin, Germany.

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Wilkosz, B., Kunte, R., Schwarz, P. et al. Numerical and experimental investigation of an impeller tip clearance variation in an aero-engine centrifugal compressor with close-coupled pipe-diffuser. CEAS Aeronaut J 5, 171–183 (2014). https://doi.org/10.1007/s13272-014-0098-z

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