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Research Papers

Numerical Investigation of the Unsteady Flow Inside a Centrifugal Compressor Stage With Pipe Diffuser

[+] Author and Article Information
Peter Jeschke

Institute of Jet Propulsion and Turbomachinery,
RWTH Aachen University,
Aachen 52062, Germany

Reinhard Niehuis

Institute of Jet Propulsion,
University of Federal Armed Forces Munich,
Neubiberg 85577, Germany

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received May 8, 2013; final manuscript received June 12, 2013; published online September 26, 2013. Editor: David Wisler.

J. Turbomach 136(3), 031012 (Sep 26, 2013) (14 pages) Paper No: TURBO-13-1071; doi: 10.1115/1.4024873 History: Received May 08, 2013; Revised June 12, 2013

The subject of this paper is the investigation of unsteady flow inside a transonic centrifugal compressor stage with a pipe-diffuser by utilizing unsteady 3D Reynolds-averaged Navier–Stokes simulations (unsteady 3D URANS). The computational fluid dynamics (CFD) results obtained are compared with detailed experimental data gathered using various steady and unsteady measurement techniques. The basic phenomena and mechanisms of the complex and highly unsteady flow inside the compressor with a pipe-diffuser are presented and analyzed in detail.

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References

Figures

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Fig. 6

Total pressure ratio and efficiency versus mass flow

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Fig. 7

Relative Mach number and absolute velocity angle distribution at the impeller exit

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Fig. 5

Grid of the compressor stage

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Fig. 4

Geometry of the diffuser and characteristic positions and planes

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Fig. 3

Picture of the compressor stage

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Fig. 2

Vortex generation inside the pipe [6]

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Fig. 1

Designation of diffuser geometry [6]

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Fig. 8

Static pressure at the diffuser shroud along the pipe centerline (x/l = 0: diffuser leading edge)

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Fig. 14

Unsteady static pressure distribution on the impeller main and splitter blade at midspan for OP B

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Fig. 9

Total pressure in front of the diffuser throat: CFD versus experimental data

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Fig. 10

Time-averaged 2D-velocity distribution behind the diffuser throat: CFD versus PIV data

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Fig. 11

Contours of the time-averaged static pressure, absolute Mach number, and total pressure inside the diffuser at midspan for OP B

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Fig. 12

Locations of the cutting planes perpendicular to the pipe axis

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Fig. 13

Time-averaged total pressure contours and velocity vectors on the cutting planes at OP B

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Fig. 15

Static pressure and unsteady deviations from the time-average of various quantities inside the impeller at midspan for OP B at a certain point in time

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Fig. 16

Unsteady static pressure at different positions of the impeller and diffuser front wall

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Fig. 17

Unsteady 2D-velocity distribution behind the diffuser throat: CFD versus PIV data (OP B)

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Fig. 18

Unsteady Mach number contours at midspan for one blade passage (OP B)

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Fig. 19

Unsteady static pressure contours at midspan for one blade passage (OP B)

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Fig. 20

Various quantities inside the diffuser at midspan for OP B at t = 1/8TD

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Fig. 21

Unsteady total pressure contours and velocity vectors on cutting planes 1, 3, and 4

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