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Abstract

As the aircraft cruising at high altitude over 20,000 m with subsonic speed, the Reynolds number in terms of the compressor blade becomes very low and the compressor performance decreases dramatically due to separation of boundary layer and secondary-flow. The main objective in this paper is to understand the physical mechanism by which Reynolds number affects the compressor stable range. In this paper, a series of steady and unsteady numerical simulations were carried out for a transonic compressor rotor under several conditions, which corresponded to the operations at sea level, and at high altitude. Detailed analyses of the flow visualization have exposed the different flow topologies of the complicated secondary flow. It was found that the transonic axial-flow compressor rotor used in current investigation was prone to tip stall behavior, and the complex flow mechanisms which occur near the blade tip are found to be the key factors for the limited flow stability both under high Reynolds number and low Reynolds number. Under high Reynolds number, the tip flow field was dominated by the low momentum zones generated by the interaction between tip leakage flow and incoming flow, and with the decrease of Reynolds number, the tip leakage flow was weakened and the low-momentum fluid due to the surface boundary layer separation and radial transport of low-energy fluid was dominant in the tip flow.

Keywords

Low Reynolds number transonic compressor flow stability numerical simulation

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References

Camp

Day

. A study of spike and modal stall phenomena in a low-speed axial compressor. ASME J Turbomachin 1998; 120: 393–401.

Wisler

. Loss reduction in axial-flow compressors through low-speed modal testing. ASME J Eng Gas Turbine Power 1985; 107: 354–363.

Mailach

. Experimental investigation of rotating instability in a low-speed research compressor. IMech 1999; C557/006: 595–604.

Zhang

Deng

Lin

. Unsteady tip leakage flow in an isolated axial compressor rotor. J Thermal Sci 2005; 14: 211–219.

Furukawa M, Saiki K, Yamada K, et al. Unsteady flow behavior due to breakdown of tip leakage vortex in an axial compressor rotor at near-stall condition. In: ASME conference on turbomachinery, Munich, Germany, 8–11 May 2000, paper no. GT-2000-666.

Yamada K, Furukawa M, Inoue M, et al. Unsteady three-dimensional flow phenomena due to breakdown of tip leakage vortex in a transonic axial compressor rotor. In: ASME conference on turbomachinery, Vienna, Austria, 14–17 June 2004, Paper no. GT2004-53745.

Tan

Greitzer

. Criteria for spike initiated rotating stall. ASME J Turbomach 2008; 130: 1–9.

Lu X, Zhu J, Chu W, et al. Mechanism of the interaction between casing treatment and tip leakage flow in a subsonic compressor. In: ASME conference on turbomachinery, Barcelona, Spain, 8–11 May 2006, Paper no. GT2006-90077.

Zhao SF, Lu XG, Zhu JQ, et al. Investigation for effects of circumferential grooves on the unsteadiness of tip clearance flow to enhance compressor flow instability. In: ASME conference on turbomachinery, Glasgow, UK, 14–18 June 2010, Paper no. GT2010-22652.

10.

Muller MW and Schiffer H-P. Effect of circumferential grooves on the aerodynamic performance of an axial single-stage transonic compressor. In: ASME conference on turbomachinery, Montreal, Canada, 14–17 May 2007, Paper no. GT2007-27365.

11.

McDougal

. A comparison between the design point and near-stall performance of an axial compressor. J Turbomach 1990; V112: 109–115.

12.

Choi M and Baek JH. Role of the hub-corner-separation on the rotating stall. In: AIAA paper, 2006, pp.2006–4462.

13.

LeJambre

Zacharias

Biederman

. Development and application of a multistage Navier–Stokes flow solver: Part II—Application to a high-pressure compressor design. ASME J Turbomach 1995; 120: 215–223.

14.

Gbadebo

Cumpsty

Hynes

. Control of three-dimensional separations in axial compressors by tailored boundary layer suction. ASME J Turbo 2007; 130: 011004–011004.

15.

Wassell

. Reynolds number effects in axial compressors. ASME J Eng Power 1968; 90: 149–156.

16.

Menter FR and Langtry RB. A Correlation-based Transition Model Using Local Variables: Part I- Model Formulation, In: ASME conference on turbomachinery, In: ASME conference on Heat Transfer, Vienna, Austria, 14–17 June 2004, Paper no. 2004-GT-53452.

17.

Langtry RB and Menter FR. A correlation-based transition model using local variables: Part II-Test Cases and Industry Applications, In: ASME conference on Heat Transfer, Vienna, Austria, 14–17 June 2004, Paper no. 2004-GT-53454.

18.

Zhao SF. Design and complex flow mechanism investigation on an axial-flow fan of small turbofan engine used in UAV. PhD thesis, Chinese Academy of Sciences, 2011.

19.

Rain DA. Tip clearance flow in axial flow compressor and pumps. Laboratories Report No.5. California Institute of Technology, Hydrodynamics and Mechanical Engineering, 1954.

Effects of low Reynolds number on flow stability of a transonic compressor

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