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Technical Brief

Optimization of the Efficiency of Stall Control Using Air Injection for Centrifugal Compressors—Additional Findings

[+] Author and Article Information
Taher Halawa

Mechanical Power Engineering Department,
Cairo University,
Giza 12613, Egypt
e-mails: taherhalawa@yahoo.com;
taherhalawa@eng.cu.edu.eg

Contributed by the Turbomachinery Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received February 18, 2018; final manuscript received February 18, 2018; published online August 9, 2018. Editor: David Wisler.

J. Eng. Gas Turbines Power 140(12), 124501 (Aug 09, 2018) (4 pages) Paper No: GTP-18-1074; doi: 10.1115/1.4039820 History: Received February 18, 2018; Revised February 18, 2018

This study presents additional important findings to the results of the research paper; “Optimization of the efficiency of stall control using air injection for centrifugal compressors” published in the Journal of Engineering for Gas Turbines and Power in 2015 (Halawa, T., Gadala, M. S., Alqaradawi, M., and Badr, O., 2015, “Optimization of the Efficiency of Stall Control Using Air Injection for Centrifugal Compressors,” ASME J. Eng. Gas Turbines Power, 137(7), p. 072604). The aim of this study is to make a fine determination of the injection angle, which provides the best stable condition when the compressor operates close to stall condition. A relatively narrower range of injection angles with smaller intervals was selected comparing to the results of the referred published paper, which clarified that the best injection angle is 30 deg. External air was injected close to the diffuser entrance at the shroud surface. Injection was applied with mass flow rate equals 1.5% of the design compressor inlet mass flow rate with injection angles ranged from 16 deg to 34 deg measured from the tangential direction at the vaneless region. It was found that both of injection angles of 28 deg and 30 deg achieved the best results in terms of compressor stabilization but each one of them has a specific advantage comparing to the other one. Using injection angle of 28 deg provided the lowest kinetic energy losses while the best orientation of the fluid through diffuser resulted when using an injection angle of 30 deg.

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References

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Figures

Grahic Jump Location
Fig. 1

NASA CC3 compressor [15]

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Fig. 2

Mach number variation with the radial coordinates for various injection angles

Grahic Jump Location
Fig. 3

Average Mach number values at three different sections for various injection angles

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Fig. 4

Percentage drop in kinetic energy in the vaneless diffuser for various injection angles

Grahic Jump Location
Fig. 5

Fluid angle at the diffuser inlet for various injection angles

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