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Research Papers: Flows in Complex Systems

Experimental and Numerical Analysis of Different Unsteady Modes in a Centrifugal Compressor With Variable Vaned Diffuser

[+] Author and Article Information
Xiang Xue

Gas Turbine Research Institute,
Shanghai Jiao Tong University,
Shanghai 200240, China
e-mail: 422529645@qq.com

Tong Wang

Gas Turbine Research Institute,
Shanghai Jiao Tong University,
Shanghai 200240, China
e-mail: twang@sjtu.edu.cn

Yuchang Shao

Gas Turbine Research Institute,
Shanghai Jiao Tong University,
Shanghai 200240, China
e-mail: yuchang.shao@carrier.utc.com

Bo Yang

Gas Turbine Research Institute,
Shanghai Jiao Tong University,
Shanghai 200240, China
e-mail: byang0626@sjtu.edu.cn

Chuangang Gu

Gas Turbine Research Institute,
Shanghai Jiao Tong University,
Shanghai 200240, China
e-mail: cggu@126.com

1Corresponding author.

Contributed by the Fluids Engineering Division of ASME for publication in the JOURNAL OF FLUIDS ENGINEERING. Manuscript received July 16, 2018; final manuscript received March 20, 2019; published online May 8, 2019. Assoc. Editor: Satoshi Watanabe.

J. Fluids Eng 141(10), 101106 (May 08, 2019) (11 pages) Paper No: FE-18-1477; doi: 10.1115/1.4043273 History: Received July 16, 2018; Revised March 20, 2019

The flow instability always varies within different compressors; however, even in one compressor, there may be still multiple various unsteady modes. To study the triggering mechanism for these unsteady modes, a detailed experimental research on an industrial centrifugal compressor with variable vaned diffuser is performed from design point to surge. The multiposition dynamic pressure measurement is conducted during the whole valve-adjusting process. The characteristics of pressure fields under some specific operating conditions are focused on, especially the prestall, stall and surge conditions. According to the collected data, the features of different unsteady modes can be obtained, such as the surge pattern and the propagation direction of stall cells. In addition, when the diffuser vane setting angle (DVA) is adjusted, the core factors to trigger total instability will change. To better complement the experimental analysis, a multipassage numerical simulation is carried out. Based on the agreement of performance curves obtained by the two methods, the flow field characteristics in the prestall state shown in the simulation results are indeed a good complement to the dynamic experimental analysis. Meanwhile, with the help of dynamic mode decomposition (DMD) method, a few low-frequency unsteady structures are extracted from the transient numerical result over a long time, which correlate with the experimental result. Through detailed analysis, an insight into the different unsteady modes in a centrifugal compressor with variable vaned diffuser is obtained.

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Figures

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Fig. 3

Performance maps of test compressor at two different DVAs

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Fig. 2

Layout of dynamic pressure sensors

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Fig. 1

Schematic display of the performance test system

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Fig. 4

Dynamic back-pressure signals from the design condition to surge at DVA = 15 deg

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Fig. 5

Pressure fluctuation mode at each radial position during surge ((a) DVA = 15 deg and (b) DVA = 27 deg)

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Fig. 6

Periodic instabilities at different circumferential positions in the vaneless region

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Fig. 7

Overviews of computational domain and mesh

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Fig. 8

Normalized Q contour near tip clearance at prestall condition ((a) at DVA = 15 deg and (b) at DVA = 27 deg)

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Fig. 9

Three-dimensional vortex structures with normalized Q =5 at prestall condition ((a) at DVA = 15 deg and (b) at DVA = 27 deg)

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Fig. 10

Spanwise streamlines in the diffuser at prestall condition ((a) at DVA = 15 deg and (b) at DVA = 27 deg)

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Fig. 11

Propagation of vortex near the impeller tip clearance at DVA = 15 deg ((a) t =0 rev; (b) t =1/32 rev; (c) t =1/16 rev; (d) t =3/32 rev; and (e) t =1/8 rev)

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Fig. 12

Modal decomposition spectra ((a) at DVA = 15 deg and (b) at DVA = 27 deg)

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Fig. 13

Pressure field modes of two specific frequencies near shroud ((a) at DVA = 15 deg, f =260 Hz, in the impeller rear region; (b) at DVA = 15 deg, f =260 Hz, in the diffuser; and (c) at DVA = 27 deg, f =50 Hz, in the impeller rear region)

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