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Technical Brief

Design Work of a Compressor Stage Through High-To-Low Speed Compressor Transformation

[+] Author and Article Information
Zhang Chenkai

Jiangsu Province Key Laboratory
of Aerospace Power System,
College of Energy and Power Engineering,
Nanjing University of Aeronautics and Astronautics,
Nanjing 210016, China
e-mail: zckkite2006@126.com

Hu Jun

Jiangsu Province Key Laboratory
of Aerospace Power System,
College of Energy and Power Engineering,
Nanjing University of Aeronautics and Astronautics,
Nanjing 210016, China
e-mail: hjape@nuaa.edu.cn

Wang Zhiqiang

Jiangsu Province Key Laboratory
of Aerospace Power System,
College of Energy and Power Engineering,
Nanjing University of Aeronautics and Astronautics,
Nanjing 210016, China
e-mail: wangzq1981@126.com

Gao Xiang

Jiangsu Province Key Laboratory
of Aerospace Power System,
College of Energy and Power Engineering,
Nanjing University of Aeronautics and Astronautics,
Nanjing 210016, China
e-mail: abrahamgx@gmail.com

1Corresponding author.

Contributed by the Turbomachinery Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received December 14, 2013; final manuscript received January 11, 2014; published online January 31, 2014. Editor: David Wisler.

J. Eng. Gas Turbines Power 136(6), 064501 (Jan 31, 2014) (7 pages) Paper No: GTP-13-1451; doi: 10.1115/1.4026520 History: Received December 14, 2013; Revised January 11, 2014

Low-speed model testing has advantages such as great accuracy and low cost and risk, so it is widely used in the design procedure of the high pressure compressor (HPC) exit stage. The low-speed model testing project is conducted in Nanjing University of Aeronautics and Astronautics (NUAA) to represent aerodynamic load and flow field structure of the seventh stage of a high-performance ten-stage high-pressure compressor. This paper outlines the design work of the low speed four-stage axial compressor, the third stage of which is the testing stage. The first two stages and the last stage provide the compressor with entrance and exit conditions, respectively. The high-to-low speed transformation process involves both geometric and aerodynamic considerations. Accurate similarities demand the same Mach number and Reynolds number, which will not be maintained due to motor power/size and its low-speed feature. Compromises of constraints are obvious. Modeling principles are presented in high-to-low speed transformation. Design work was carried out based on these principles. Four main procedures were conducted successively in the general design, including establishment of low-speed modeling target, global parameter design of modeling stage, throughflow aerodynamic design, and blading design. In global parameter design procedure, rotational speed, shroud diameter, hub-tip ratio, midspan chord, and axial spacing between stages were determined by geometrical modeling principles. During the throughflow design process, radial distributions of aerodynamic parameters such as D-factor, pressure-rise coefficient, loss coefficients, stage reaction, and other parameters were obtained by determined aerodynamic modeling principles. Finally, rotor and stator blade profiles of the low speed research compressor (LSRC) at seven span locations were adjusted to make sure that blade surface pressure coefficients agree well with that of the HPC. Three-dimensional flow calculations were performed on the low-speed four-stage axial compressor, and the resultant flow field structures agree well with that of the HPC. It is worth noting that a large separation zone appears in both suction surfaces of LSRC and HPC. How to diminish it through 3D blading design in the LSRC test rig is our further work.

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References

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Figures

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Fig. 1

Flow chart of high-pressure compressor aerodynamic design

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Fig. 2

Comparisons of radial distributions of high and low-speed rotor and stator exit axial velocity coefficients

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Fig. 3

Comparisons of radial distributions of high and low-speed rotor and stator D-factors

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Fig. 4

Comparisons of radial distributions of high and low-speed rotor and stator total pressure loss coefficients

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Fig. 5

Comparisons of radial distributions of stage total pressure-rise coefficient and reaction

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Fig. 6

Comparisons of radial distributions of rotor inlet and outlet absolute flow angles

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Fig. 7

Comparisons of radial distributions of rotor inlet and outlet relative flow angles

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Fig. 8

Basic flow chart of LSRC blading design

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Fig. 9

Surface pressure coefficient distributions of rotor and stator blade sections: (a) rotor and (b) stator

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Fig. 10

Low-speed 3D rotor and stator blade profiles

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Fig. 11

Comparisons of tip and hub section profiles of high and low-speed stages: (a) HPC and (b) LSRC

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Fig. 12

Comparisons of high and low-speed rotor and stator blade surface limiting streamlines: (a) rotor and (b) stator

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