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Design of a sub-scale fan for a boundary layer ingestion test with by-pass flow

Published online by Cambridge University Press:  17 August 2022

H. Mårtensson Open the ORCID record for H. Mårtensson [Opens in a new window] ,
M. Lejon ,
D. Ghosh ,
M. Åkerberg ,
F. Rasimarzabadi  and
M. Neuteboom
H. Mårtensson*
Affiliation:
GKN Aerospace Engine Systems, Trollhättan, Sweden
M. Lejon
Affiliation:
GKN Aerospace Engine Systems, Trollhättan, Sweden
D. Ghosh
Affiliation:
Chalmers University, Gothenburg, Sweden
M. Åkerberg
Affiliation:
Chalmers University, Gothenburg, Sweden
F. Rasimarzabadi
Affiliation:
National Research Council of Canada, Ottawa, Canada
M. Neuteboom
Affiliation:
National Research Council of Canada, Ottawa, Canada
*
*Corresponding author. Email: hans.martensson@gknaerospace.com
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Abstract

A design of a sub-scale Boundary Layer Ingestion (BLI) fan for a transonic test rig is presented. The fan is intended to be used in flow conditions with varying distortion patterns representative of a BLI application on an aircraft. The sub-scale fan design is based on a design study of a full-scale fan for a BLI demonstration project for a Fokker 100 aircraft. CFD results from the full-scale fan design and the ingested distortion pattern from CFD analyses of the whole aircraft are used as inputs for this study. The sub-scale fan is designed to have similar performance characteristics to the full-scale fan within the capabilities of the test facility. The available geometric rig envelope in the test facility necessitates a reduction in geometric scale and consideration of the operating conditions. Fan blades and vanes are re-designed for these conditions in order to mitigate the effects of the scaling. The effects of reduced size, increased relative tip clearance and thicknesses of the blades and vanes are evaluated as part of the step-by-step adaption of the design to the sub-scale conditions. Finally, the installation effects in the rig are simulated including important effects of the by-pass flow on the running characteristics and the need to control the effective fan nozzle area in order to cover the available fan operating range. The predicted operating behaviour of the fan as installed in the coming transonic test rig gives strong indication that the sub-scale fan tests will be successful.

Keywords

DistortionBoundary layer ingestionFan
Type
Research Article
Information
The Aeronautical Journal , Volume 126 , Issue 1302: The 25th ISABE Conference Special Issue – Part II , August 2022 , pp. 1288 - 1302
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Copyright
© The Author(s), 2022. Published by Cambridge University Press on behalf of Royal Aeronautical Society

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Footnotes

This paper is a version of a presentation due to be given at the 2022 ISABE Conference

References

Smith, A. and Roberts, H. The jet airplane using boundary layer air for propulsion, J. Aeronaut. Sci. 1947; 14, 2, 97–109.Google Scholar
Smith, L.H. Jr. Wake ingestion propulsion benefit, J. Propuls. Power, 1993; 9, 1, 74–82.CrossRefGoogle Scholar
Plas, A.P., Sargeant, M.A., Madani, V., Crichton, D., Greitzer, E.M., Hynes, T.P., Hall, C.A., Performance of a boundary layer ingesting (BLI) propulsion system, 45th AIAA Aerospace Sciences Meeting and Exhibit, 8–11 January 2007, Reno, Nevada.CrossRefGoogle Scholar
Drela, M. Development of the D8 transport configuration, Paper 2011-3970, 29th AIAA Applied Aerodynamics conference, 27–30 June 2011, Honolulu, HI, USA.CrossRefGoogle Scholar
Uranga, A., Drela, M., Greitzer, E., Titchener, N., Lieu, M., Siu, N., Huang, A., Gatlin, G., Hannon, J., Preliminary experimental assessment of the boundary layer ingestion benefit for the D8 aircraft, Proceedings of the 52nd Aerospace Sciences Meeting, AIAA SciTech Forum AIAA 2014-0906, National Harbor, MD, USA, 13–17, January 2014, doi: 10.2514/6.2014-0906.CrossRefGoogle Scholar
Celestina, M. and Long-Davis, M. Large-scale boundary layer ingesting propulsor research, ISABE-2019-24264, Proceedings of the 24th ISABE conference, Canberra, Australia, 2019.Google Scholar
Welstead, J. and Felder, J. Conceptual design of a single-aisle turboelectric commercial transport with fuselage boundary layer ingestion, 54th AIAA Aerospace Sciences Meeting, doi: 10.2514/6.2016-1027, 2016.CrossRefGoogle Scholar
Seitz, A., Peter, F., Bijewitz, J., Habermann, A., Goraj, Z., Kowalski, M., Castillo Pardo, A., Hall, C.A., Meller, F., Merkler, R., Petit, O., Samuelsson, S., Della Corte, B., van Sluis, M., Wortmann, G. and Dietz, M. Concept validation study for fuselage wake filling propulsion integration, 31st Congress of the International Council of the Aeronautical Sciences, International Council of Aeronautical Sciences, Sept. 2018.Google Scholar
Pardo, A. and Hall, C. Aerodynamics of boundary layer ingesting fuselage fans, ISABE-2019-24162, Proceedings of the 24th ISABE conference, Canberra, Australia, 2019.Google Scholar
Gunn, E. and Hall, C. Aerodynamics of boundary layer ingesting fans, GT2014-26142, Proceedings of ASME Turbo Expo, 2014.CrossRefGoogle Scholar
Provenza, A., Duffy, K., Bakhle, M., Aeromechanical response of a distortion tolerant boundary layer ingesting fan, GT2018-77094, Proceedings of ASME Turbo Expo, 2018.CrossRefGoogle Scholar
Rasimarzabadi, F. Engine inlet velocity profile effects- design part, Report No.: LTR-GTL-2020-0077, National Research Council Canada, Gas Turbine Laboratory, 2020.Google Scholar
Mårtensson, H. and Laban, M. Design and performance of a boundary layer ingestion fan. Proceedings of ASME Turbo Expo 2020 virtual conference. GT2020-15479, June 2020.Google Scholar
Mårtensson, H., Ellbrant, L. and Lundbladh, A. Design conditions for an aft mounted fan with boundary layer ingestion, ISABE-2019-24258.Google Scholar
Sakulkaew, S., Tan, C.S., Donahoo, E., Cornelius, C. and Montgomery, M. Compressor efficiency variation with rotor tip gap from vanishing to large clearance, ASME. J. Turbomach. 2013, 135, 3, p 031030. https://doi.org/10.1115/1.4007547CrossRefGoogle Scholar
Copenhaver, W.W., Mayhew, E.R., Hah, C. and Wadia, A.R. The effect of tip clearance on a swept transonic compressor rotor, ASME. J. Turbomach. 1996; 118, 2, 230–239. https://doi.org/10.1115/1.2836630CrossRefGoogle Scholar