Effects of inlet radial distortion on the type of stall precursor in low-speed axial compressor

Abstract

Experimental investigations of the effect of inlet blade loading on the rotating stall inception process are carried out on a single-stage low-speed axial compressor. Temporal pressure signals from the six high response pressure transducers are used for the analysis. Pressure variations at the hub are especially recorded during the stall inception process. Inlet blade loading is altered by installing metallic meshed distortion screens at the rotor upstream. Three sets of experiments are performed for the comparison of results, i.e. uniform inlet flow, tip, and hub distortions, respectively. Regardless of the type of distortion introduced to the inflow, the compressor undergoes a performance drop, which is more severe in the hub distortion case. Under the uniform inlet flow condition, stall inception is caused by the modal type disturbance while the stall precursor switched to spike type due to the highly loaded blade tip. In the presence of high blade loading at the hub, spike disappeared and the compressor once again witnessed a modal type disturbance. Hub pressure fluctuations are observed throughout the process when the stall is caused by a modal wave while no disturbance is noticed at the hub in spike type stall inception. It is believed that the hub flow separation contributes to the modal type of stall inception phenomenon. Results are also supported by the recently developed signal processing techniques for the stall inception study.

Keywords

Low-speed compressor radial distortion stall inception stall precursor blade loading

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References

Emmons

Pearson

Grant

. Compressor surge and stall propagation. Trans ASME 1955; 77: 455–469.

Greitzer

. Surge and rotating stall in axial flow compressors—Part I: Theoretical compression system model. J Eng Gas Turbines Power 1976; 98: 190–198.

Greitzer

. Surge and rotating stall in axial flow compressors—Part II: Experimental results and comparison with theory. J Eng Gas Turbines Power 1976; 98: 199–211.

Day

. Active suppression of rotating stall and surge in axial compressors. ASME J Turbomach 1993; 115: 40–47.

Cumpsty

. Compressor aerodynamics, Malabar, FL: Krieger Publishing Company, 2004, pp. 359–409.

Camp

Day

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

Freeman

Wilson

Day

et al.

Experiments in active control of stall on an aeroengine gas turbine. ASME J Turbomach 1998; 120: 637–647.

Day

. Stall inception in axial flow compressors. ASME J Turbomach 1993; 115: 1–9.

Greitzer

. Some aerodynamic problems of aircraft engines: Fifty years after-the 2007 IGTI scholar lecture. ASME J Turbomach 2007; 131: 031101–031101.

10.

Moore

Greitzer

. A theory of post-stall transients in axial compression systems: Part I-Development of equations. J Eng Gas Turbines Power 1986; 108: 68–76.

11.

McDougall

Cumpsty

Hynes

. Stall inception in axial compressors. ASME J Turbomach 1990; 112: 116–125.

12.

Moore

. A theory of rotating stall of multistage axial compressors: Part I—Small disturbances. J Eng Gas Turbines Power 1976; 106: 313–320.

13.

Moore

. A theory of rotating stall of multistage axial compressors: Part II—Finite disturbances. J Eng Gas Turbines Power 1984; 106: 321–326.

14.

Longley

. A review of nonsteady flow models for compressor stability. ASME J Turbomach 1994; 116: 202–215.

15.

Outa E, Kato D and Chiba Y. A N-S simulation of stall cell behavior in a 2-D compressor rotor-stator system at various loads. ASME Paper No. GT1994-257, 2016.

16.

He L and Ismael JO. Computations of blade row stall inception in transonic flows. In: 13th ISABE proceedings, Chattanooga, Tennessee, USA, 7–12 September 1997, pp.697–707.

17.

Saxer-Felici HM, Saxer AP, Inderbitzin A, et al. Prediction and measurement of rotating stall cells in an axial compressor. ASME Paper No. GT1998-67, 1998.

18.

Hah

Wennerstrom

. Three-dimensional flow fields inside a transonic compressor with swept blades. ASME J Turbomach 1991; 113: 241–251.

19.

Gong

Tan

Gordon

et al.

A computational model for shour wavelength stall inception and development in multi-stage compressors. ASME J Turbomach 1999; 121: 726–734.

20.

Emmons

Pearson

Grant

. Compressor surge and stall propagation. Trans ASME 1955; 77: 455–469.

21.

Hynes

Greitzer

. A method for assessing effects of circumferential flow distortion on compressor stability. ASME J Turbomach 1987; 109: 371–379.

22.

Spakovszky

Weigl

Paduano

et al.

Rotating stall control in a high-speed stage with inlet distortion: Parts I–II. ASME J Turbomach 1999; 121: 510–524.

23.

Hah

Rabe

Sullivan

et al.

Effects of inlet distortion on the flow field in a transonic compressor rotor. ASME J Turbomach 1998; 120: 233–246.

24.

Lesser A and Niehuis R. Transonic axial compressors with total pressure inlet flow field distortions. ASME Paper No. GT2014-26627, 2014.

25.

Lucas JR, O’Brien WF and Ferrar AM. Effect of bli-type inlet distortion on turbofan engine performance. ASME Paper No. GT2014-26666, 2014.

26.

Longley

Shin

Plumley

et al.

Effects of rotating inlet distortion on multistage compressor stability. ASME J Turbomach 1996; 118: 181–188.

27.

Peters T and Fottner L. Effects of co- and counter-rotating inlet distortions on a 5-stage hp-compressor. ASME Paper No. GT2002-30395, 2002.

28.

Peters T, Burgener T and Fottner L. Effects of rotating inlet distortion on a 5-stage hp-compressor. ASME Paper No. GT2001-0300, 2001.

29.

Cameron

Scott

. Analysis of axial compressor stall inception using unsteady casing pressure measurements. ASME J Turbomach 2012; 135: 021036–1-021036-12.

30.

Li Q, Pan T, Li Z, et al. Experimental study of compressor instability inception in a transonic axial flow compressor. ASME Paper No. GT2014-25190, 2014.

31.

Pan T, Li Q, Li Z, et al. Effects of radial loading distribution on partial surge initiated instability in a transonic axial flow compressor. ASME Paper No. GT2015-42664, 2015.

32.

Jiang H, Lu L, Yuan W, et al. Experimental investigation of the influence of inlet distortion on the stall inception in a low speed axial compressor. ASME Paper No. GT2009-59139, 2009.

33.

Arshad

Pan

. Application of non filtering analytic wavelet transform for the investigation of rotating stall inception in low speed compressor. IEEE Trans 2016. DOI: 10.1109/ICMAE.2016.7549582.

34.

Davis G. Non-uniform flow through wire screens. PhD Dissertation, University of Cambridge, USA, 1957.

35.

Origin pro 9 user’s manual.

36.

Pan

Wang

. An adaptive logarithmic threshold framelet analysis of the partial surge initiated instability in a transonic axial flow compressor. Proc IMechE, Part C: J Mechanical Engineering Science 2016; 231: 3202–3213.

37.

Hah

Loellbach

. Development of hub corner stall and its influence on the performance of axial compressor blade rows. ASME J Turbomach 1999; 12: 67–77.

38.

Lewin E, Kozulovic D and Stark U. Experimental and numerical analysis of hub-corner stall in compressor cascades. ASME Paper No. GT2010-22704, 2010.