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Open AccessArticle

Proof of Concept Study for Fuselage Boundary Layer Ingesting Propulsion

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Bauhaus Luftfahrt e.V., Willy-Messerschmitt-Str. 1, 82024 Taufkirchen, Germany
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Whittle Laboratory, University of Cambridge, 1 JJ Thomson Av., Cambridge CB30DY, UK
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Faculty of Aerospace Engineering, Delft University of Technology, 2629 Delft, The Netherlands
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Faculty of Power and Aeronautical Engineering, Warsaw University of Technology, Pl. Politechniki 1, 00-661 Warsaw, Poland
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Division of Fluid Dynamics, Department of Mechanics and Maritime Sciences, Chalmers University of Technology, 412 96 Gothenburg, Sweden
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Engineering Advanced Programs, MTU Aero Engines AG, 80995 Munich, Germany
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Rolls-Royce Electrical, Rolls Royce Deutschland Ltd., 91058 Erlangen, Germany
*
Author to whom correspondence should be addressed.
Aerospace 2021, 8(1), 16; https://doi.org/10.3390/aerospace8010016
Received: 14 December 2020 / Revised: 8 January 2021 / Accepted: 9 January 2021 / Published: 13 January 2021
Key results from the EU H2020 project CENTRELINE are presented. The research activities undertaken to demonstrate the proof of concept (technology readiness level—TRL 3) for the so-called propulsive fuselage concept (PFC) for fuselage wake-filling propulsion integration are discussed. The technology application case in the wide-body market segment is motivated. The developed performance bookkeeping scheme for fuselage boundary layer ingestion (BLI) propulsion integration is reviewed. The results of the 2D aerodynamic shape optimization for the bare PFC configuration are presented. Key findings from the high-fidelity aero-numerical simulation and aerodynamic validation testing, i.e., the overall aircraft wind tunnel and the BLI fan rig test campaigns, are discussed. The design results for the architectural concept, systems integration and electric machinery pre-design for the fuselage fan turbo-electric power train are summarized. The design and performance implications on the main power plants are analyzed. Conceptual design solutions for the mechanical and aero-structural integration of the BLI propulsive device are introduced. Key heuristics deduced for PFC conceptual aircraft design are presented. Assessments of fuel burn, NOx emissions, and noise are presented for the PFC aircraft and benchmarked against advanced conventional technology for an entry-into-service in 2035. The PFC design mission fuel benefit based on 2D optimized PFC aero-shaping is 4.7%. View Full-Text
Keywords: boundary layer ingestion; propulsive fuselage; wake-filling; turbo-electric; proof-of-concept; wind tunnel; fan rig; multi-disciplinary aircraft design; collaborative research boundary layer ingestion; propulsive fuselage; wake-filling; turbo-electric; proof-of-concept; wind tunnel; fan rig; multi-disciplinary aircraft design; collaborative research
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MDPI and ACS Style

Seitz, A.; Habermann, A.L.; Peter, F.; Troeltsch, F.; Castillo Pardo, A.; Della Corte, B.; van Sluis, M.; Goraj, Z.; Kowalski, M.; Zhao, X.; Grönstedt, T.; Bijewitz, J.; Wortmann, G. Proof of Concept Study for Fuselage Boundary Layer Ingesting Propulsion. Aerospace 2021, 8, 16. https://doi.org/10.3390/aerospace8010016

AMA Style

Seitz A, Habermann AL, Peter F, Troeltsch F, Castillo Pardo A, Della Corte B, van Sluis M, Goraj Z, Kowalski M, Zhao X, Grönstedt T, Bijewitz J, Wortmann G. Proof of Concept Study for Fuselage Boundary Layer Ingesting Propulsion. Aerospace. 2021; 8(1):16. https://doi.org/10.3390/aerospace8010016

Chicago/Turabian Style

Seitz, Arne; Habermann, Anaïs L.; Peter, Fabian; Troeltsch, Florian; Castillo Pardo, Alejandro; Della Corte, Biagio; van Sluis, Martijn; Goraj, Zdobyslaw; Kowalski, Mariusz; Zhao, Xin; Grönstedt, Tomas; Bijewitz, Julian; Wortmann, Guido. 2021. "Proof of Concept Study for Fuselage Boundary Layer Ingesting Propulsion" Aerospace 8, no. 1: 16. https://doi.org/10.3390/aerospace8010016

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