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Research Papers

Evolution Process of Diffuser Stall in a Centrifugal Compressor With Vaned Diffuser

[+] Author and Article Information
Nobumichi Fujisawa

Department of Applied Mechanics
and Aerospace Engineering,
Waseda University,
3-4-1, Okubo, Shinjuku-ku,
Tokyo 169-8555, Japan
e-mail: nobumichi-fuji@akane.waseda.jp

Tetsuya Inui

Department of Applied Mechanics and
Aerospace Engineering,
Waseda University,
3-4-1, Okubo, Shinjuku-ku,
Tokyo 169-8555, Japan
e-mail: ti-23.sp.at@suou.waseda.jp

Yutaka Ohta

Department of Applied Mechanics
and Aerospace Engineering,
Waseda University,
3-4-1, Okubo, Shinjuku-ku,
Tokyo 169-8555, Japan
e-mail: yutaka@waseda.jp

1Corresponding author.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received October 11, 2018; final manuscript received December 9, 2018; published online January 21, 2019. Editor: Kenneth Hall.

J. Turbomach 141(4), 041009 (Jan 21, 2019) (10 pages) Paper No: TURBO-18-1289; doi: 10.1115/1.4042249 History: Received October 11, 2018; Revised December 09, 2018

This paper describes in detailed flow field in a centrifugal compressor with a vaned diffuser at off design point. Especially, we conducted both the experimental and numerical analysis in order to investigate the evolution process of a diffuser stall. At the stall point, the diffuser stall was initiated and rotated near the shroud side in the vaneless space. Furthermore, the diffuser stall was developed to a stage stall cell, as the mass flow was decreased. The developed stall cell was rotated within both the impeller and diffuser passages. The evolution process of the diffuser stall had three stall forms. First, the diffuser stall was rotating near the shroud side. Then, the diffuser stall shifted to the hub side and moved into the impeller passages. Finally, a stage stall was generated. From computational fluid dynamics (CFD) analysis, a tornado-type vortex was generated first, near the hub side of the diffuser leading edge, when the diffuser stall was shifted to the hub side. Next, a throat area blockage was formed near the hub side because of the boundary layer separation in the vaneless space. Finally, the blockage within the diffuser passages expanded to the impeller passages and developed into a stage stall. From the pressure measurements along the impeller and diffuser passages, the magnitude of pressure fluctuation on the casing wall of the diffuser throat area also suddenly increased when the diffuser stall shifted to the hub side. Therefore, the evolution area of the diffuser stall was caused by the evolution of the blockage near the throat area of the diffuser passage.

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Figures

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Fig. 1

Illustration of the rotating mechanism of the diffuser stall cell [12]

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Fig. 2

Configuration of compressor geometry and pressure measuring system

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Fig. 3

Overview of the computational grid

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Fig. 4

Compressor performance

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Fig. 5

Distribution of velocity fluctuations in spanwise direction

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Fig. 6

Radial velocity and pressure fluctuation traces at the diffuser inlet (ϕ = 0.10, 30 Hz low-pass filter)

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Fig. 7

Spanwise radial velocity distribution of the impeller-discharge flow in conditions (a) and (b)

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Fig. 8

Distribution of velocity fluctuation in spanwise direction in three conditions (a)–(c)

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Fig. 9

Power spectra of pressure fluctuations in impeller passage

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Fig. 10

Mass flow fluctuations at diffuser throat area

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Fig. 11

Mass flow fluctuations at impeller inlet

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Fig. 12

Mass flow fluctuations at the diffuser passage no. 10 throat area

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Fig. 13

Instantaneous absolute pressure distributions between the impeller exit and diffuser leading edge and vortical structure of the diffuser stall within stalled diffuser passages in condition (a)

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Fig. 14

Instantaneous absolute velocity distributions on hub side within diffuser passage nos. 8–11 in condition (b)

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Fig. 15

Instantaneous vortical structure within diffuser passage nos. 8–11 in condition (b)

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Fig. 16

Visualization plane of the meridian section within the impeller and diffuser passages

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Fig. 17

Instantaneous entropy contour of the meridian section and drawing of vortex streamlines in conditions (a)–(c)

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Fig. 18

Instantaneous vortical structure within the impeller passages in condition (c)

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Fig. 19

Pressure fluctuation traces (30 Hz low-pass filter) and RMS of pressure fluctuation along the compressor meridional direction

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