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An altitude capable rig for studying engine inlet velocity profile effects: Boundary layer generator

Part of: The AJ Propulsion Collection

Published online by Cambridge University Press:  28 July 2022

F. Rasimarzabadi Open the ORCID record for F. Rasimarzabadi [Opens in a new window] ,
C. Clark ,
M. Neuteboom ,
D. Orchard  and
H. Martensson
F. Rasimarzabadi*
Affiliation:
National Research Council of Canada, Ottawa, Ontario, Canada
C. Clark
Affiliation:
National Research Council of Canada, Ottawa, Ontario, Canada
M. Neuteboom
Affiliation:
National Research Council of Canada, Ottawa, Ontario, Canada
D. Orchard
Affiliation:
National Research Council of Canada, Ottawa, Ontario, Canada
H. Martensson
Affiliation:
GKN Aerospace Engine Systems, Trollhattan, Sweden
*
*Corresponding author. Email: [email protected]
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Abstract

A new aerodynamic open-circuit test rig for studying boundary layer ingestion (BLI) propulsion has been developed by National Research Council of Canada. The purpose is to demonstrate the advantages of BLI in reducing the power required for a given thrust and to validate the performance of BLI fan concepts. The rig consists of a boundary layer generator to simulate boundary layer development over an aircraft fuselage. The boundary layer generator can be used to create a natural boundary layer due to skin friction but also comprises an array of perforated plates through which pressurised air can be blown to manipulate the boundary layer thickness. The size of the boundary layer thickness can be controlled upstream of the fan blades. Parametric studies of boundary layer thickness were then feasible. The test calibration was conducted to validate the concept.

Keywords

Boundary layer ingestionBoundary layer generatorFan
Type
Research Article
Information
The Aeronautical Journal , Volume 126 , Issue 1302: The 25th ISABE Conference Special Issue – Part II , August 2022 , pp. 1430 - 1446
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Copyright
© The Author(s), 2022. Published by Cambridge University Press on behalf of Royal Aeronautical Society

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References

Seitz, A., Bijewitz, J., Kaiser, S. and Wortman, G. Conceptual investigation of a propulsive fuselage aircraft layout, Aircr. Eng. Aerosp. Technol. Int. J., 2014, 86, (6), pp 464–472.CrossRefGoogle Scholar
Hall, D.K., Huang, A.C., Uranga, A., Greitzer, E.M., Drela, M. and Sato, S. Boundary layer ingestion propulsion benefit for transport aircraft, J. Propul. Power, 2017, 33, (5).CrossRefGoogle Scholar
Smith, L.H. Wake ingestion propulsion benefit, AIAA J. Propul. Power, 1993, 9, (1), pp 74–82.CrossRefGoogle Scholar
Tillman, T.G., Hardin, L.W., Moffitt, B.A., Sharma, O.P., Lord, W.K., Berton, J. and Arend, D. System-level benefits of boundary layer ingesting propulsion, AIAA 49 th Aerospace Sciences Meeting, 2011.Google Scholar
Liebeck, R.H. Design of the blended wing body subsonic transport, Journal of Aircraft, 2004, 41, (1), pp 10–25.CrossRefGoogle Scholar
Kawai, R.T., Friedman, D.M. and Serrano, L. Blended wing body (BWB) boundary layer ingestion (BLI) inlet configuration and system studies, NASA/CR-2006-214534, 2006.Google Scholar
Florea, R.V., Matalantis, C., Hardin, L.W., Stucky, M., Shabbir, A., Sharma, O. and Arend, D. Parametric analysis and design for embedded engine inlets, 49 th AIAA/SAE/ASEE Joint Propulsion Conference, AIAA 2012-3994, 2012.CrossRefGoogle Scholar
Rhodes, G.D. Experimental investigation of the propulsive fuselage concept, MSc. Thesis, Graduate School of the Ohio State University, 2018.Google Scholar
Plas, A. Performance of a boundary layer ingesting propulsion system, MSc. Thesis, Massachusetts Institute of Technology, 2006.CrossRefGoogle Scholar
Currie, T. Development of a small modular multi-stage axial compressor for ice crystal icing research, AIAA Aviation Forum, AIAA-2018-4133, 2018.CrossRefGoogle Scholar
Martensson, H., Lejon, M., Ghosh, D., Akerberg, M., Rasimarzabadi, F. and Neuteboom, M. Design of a sub-scale fan for a boundary layer ingestion test with by-pass flow, The Aeronautical Journal, 2021.Google Scholar
Martensson, H. and Laban, M.M. Design and performance of a boundary layer ingestion fan, Proceedings of ASME Turbo Expo 2020 virtual conference, GT2020-15479, June 2020.Google Scholar
Orchard, D.M. and Clark, C., Engine iNlet VELOcity Profile Effects (ENVELOPE): Artificial Thickening of Approaching Boundary Layer, Report No.: LM-AL-2019-0049, National Research Council Canada, Aerodynamics Laboratory, 2019.Google Scholar
Ansys Fluent Workbench Tutorial Guide, 2021R2, ANSYS Inc., 2021.Google Scholar
Roe, P. Characteristic-based schemes for the Euler equations, Ann. Rev. Fluid Mech., 2003, 18, (1), pp 337–365, doi: 10.1146/annurev.fl.18.010186.002005 CrossRefGoogle Scholar
Launder, B.E. and Spalding, D.B. The numerical computation of turbulent flows, Comput. Methods Appl. Mech. Eng., 1974, 3, pp 269–289.CrossRefGoogle Scholar
Piquet, J. Turbulent Flows Models and Physics, Springer Berlin Heidelberg, 2013, ISBN: 9783662035597, 3662035596.Google Scholar
Martensson, H. Harmonic forcing from distortion in a boundary layer ingesting fan, Aerospace, 2021, 8, (3), p 58, doi: 10.3390/aerospace8030058 CrossRefGoogle Scholar