Jet engines with boundary layer ingestion (BLI) could offer significant reductions in aircraft fuel burn compared with podded turbofans. However, the engine fans must run continuously with severe inlet distortion, which is known to reduce stability. In this paper, an experimental study has been completed on a low-speed rig fan operating with a BLI-type inlet distortion. Unsteady casing static pressure measurements have been made at multiple locations during stall events. Steady-state, full-annulus area traverses have also been performed at rotor inlet and exit at a near-stall operating point. The reduction in stability caused by BLI is found to be small. It is found that with BLI the fan can operate stably despite the presence of localized regions where the rotor operating point lies beyond the stability boundary measured in clean flow. With the BLI-type distortion applied, the measured rotor incidence varies around the annulus due to nonuniform upstream velocity and swirl. The measured amplitude of unsteady casing pressure fluctuations just prior to stall is found to correlate with the circumferential variation of rotor incidence, suggesting that rotor incidence is a key variable affecting the creation and growth of flow disturbances. In regions of high incidence, disturbances resembling local flow separations are initiated. However, in regions of low or negative incidence, any disturbances decay rapidly. Full rotating stall with BLI occurs when high incidence regions are widespread enough to sustain disturbances which can propagate around the entire annulus.
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September 2019
Research-Article
Stall Inception in a Boundary Layer Ingesting Fan
D. Perovic,
D. Perovic
Whittle Laboratory,
1 JJ Thomson Avenue,
Cambridge CB3 0DY,
e-mail: dp420@cam.ac.uk
University of Cambridge
,1 JJ Thomson Avenue,
Cambridge CB3 0DY,
UK
e-mail: dp420@cam.ac.uk
Search for other works by this author on:
C. A. Hall,
C. A. Hall
Whittle Laboratory,
1 JJ Thomson Avenue,
Cambridge CB3 0DY,
e-mail: cah1003@cam.ac.uk
University of Cambridge
,1 JJ Thomson Avenue,
Cambridge CB3 0DY,
UK
e-mail: cah1003@cam.ac.uk
Search for other works by this author on:
E. J. Gunn
E. J. Gunn
Turbostream Ltd,
3 Charles Babbage Road,
Cambridge CB3 0GT,
3 Charles Babbage Road,
Cambridge CB3 0GT,
UK
Search for other works by this author on:
D. Perovic
Whittle Laboratory,
1 JJ Thomson Avenue,
Cambridge CB3 0DY,
e-mail: dp420@cam.ac.uk
University of Cambridge
,1 JJ Thomson Avenue,
Cambridge CB3 0DY,
UK
e-mail: dp420@cam.ac.uk
C. A. Hall
Whittle Laboratory,
1 JJ Thomson Avenue,
Cambridge CB3 0DY,
e-mail: cah1003@cam.ac.uk
University of Cambridge
,1 JJ Thomson Avenue,
Cambridge CB3 0DY,
UK
e-mail: cah1003@cam.ac.uk
E. J. Gunn
Turbostream Ltd,
3 Charles Babbage Road,
Cambridge CB3 0GT,
3 Charles Babbage Road,
Cambridge CB3 0GT,
UK
Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the Journal of Turbomachinery. Manuscript received February 11, 2019; final manuscript received April 26, 2019; published online June 12, 2019. Assoc. Editor: Kenneth Hall.
J. Turbomach. Sep 2019, 141(9): 091007 (10 pages)
Published Online: June 12, 2019
Article history
Received:
February 11, 2019
Revision Received:
April 26, 2019
Accepted:
April 26, 2019
Citation
Perovic, D., Hall, C. A., and Gunn, E. J. (June 12, 2019). "Stall Inception in a Boundary Layer Ingesting Fan." ASME. J. Turbomach. September 2019; 141(9): 091007. https://doi.org/10.1115/1.4043644
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