Research Papers

Stability Improvement of High-Pressure-Ratio Turbocharger Centrifugal Compressor by Asymmetrical Flow Control—Part II: Nonaxisymmetrical Self-Recirculation Casing Treatment

[+] Author and Article Information
Xinqian Zheng

e-mail: zhengxq@tsinghua.edu.cn

Mingyang Yang

State Key Laboratory of Automotive Safety and Energy,
Tsinghua University,
Beijing 100084, China

Hideaki Tamaki

Turbo Machinery and Engine Technology,
Department, IHI Corporation,
Yokohama, 235-8501, Japan

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNALOF TURBOMACHINERY. Manuscript received April 26, 2010; final manuscript received December 26, 2011; published online November 1, 2012. Assoc. Editor: Michael Casey.

J. Turbomach 135(2), 021007 (Nov 01, 2012) (8 pages) Paper No: TURBO-10-1039; doi: 10.1115/1.4006637 History: Received April 26, 2010; Revised December 26, 2011

This is part II of a two-part paper involving the development of an asymmetrical flow control method to widen the operating range of a turbocharger centrifugal compressor with high-pressure ratio. A nonaxisymmetrical self-recirculation casing treatment (SRCT) as an instance of asymmetrical flow control method is presented. Experimental and numerical methods were used to investigate the impact of nonaxisymmetrical SRCT on the surge point of the centrifugal compressor. First, the influence of the geometry of a symmetric SRCT on the compressor performance was studied by means of numerical simulation. The key parameter of the SRCT was found to be the distance from the main blade leading edge to the rear groove (Sr). Next, several arrangements of a nonaxisymmetrical SRCT were designed, based on flow analysis presented in part I. Then, a series of experiments were carried out to analyze the influence of nonaxisymmetrical SRCT on the compressor performance. Results show that the nonaxisymmetrical SRCT has a certain influence on the performance and has a larger potential for stability improvement than the traditional symmetric SRCT. For the investigated SRCT, the surge flow rate of the compressor with the nonaxisymmetrical SRCTs is about 10% lower than that of the compressor with symmetric SRCT. The largest surge margin (smallest surge flow rate) can be obtained when the phase of the largest Sr is coincident with the phase of the minimum static pressure in the vicinity of the leading edge of the splitter blades.

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Fig. 5

Influence of SRCT geometry on the efficiency

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Fig. 6

Influence of SRCT geometry on the recirculation flow rate

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Fig. 7

Circumferential Sr distribution for seven SRCT types

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Fig. 8

Separated shroud with SRCT and volute

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Fig. 9

Comparison of surge flow rates for compressors with symmetric SRCTs

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Fig. 4

Influence of SRCT geometry on the compressor pressure ratio

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Fig. 3

Sketch of SRCT in a centrifugal compressor

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Fig. 2

The computational domain of single passage and whole stage

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Fig. 1

Sketch of meshing approach for tip clearance

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Fig. 10

Comparison of surge flow rates for compressors with nonaxisymmetrical SRCTs

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Fig. 11

Static pressure distribution at the leading edge of the splitter blades near surge

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Fig. 12

Ms comparison for compressors with different nonaxisymmetrical SRCTs at different rotational speeds

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Fig. 13

Comparison of surge flow rate for compressors with type G SRCT and type C SRCT

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Fig. 14

Flow rate distribution in the impeller passages near surge at 100%N

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Fig. 15

Sections in compressors with SRCT

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Fig. 16

Relative flow angle distribution near main blade leading edge

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Fig. 17

Relative flow angle distribution near splitter leading edge

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Fig. 18

Static pressure distribution near the outlet of diffuser

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Fig. 19

Relative flow angle distribution near main blade leading edge




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