Proof of concept study for fuselage boundary layer ingesting propulsion

Journal article (2021)

Authors

Arne Seitz Bauhaus Luftfahrt e. V.
Anaïs Luisa Habermann Bauhaus Luftfahrt e. V.
Fabian Peter Bauhaus Luftfahrt e. V.
Florian Troeltsch Bauhaus Luftfahrt e. V.
Alejandro Castillo Pardo University of Cambridge
B. della Corte Flight Performance and Propulsion - Aerospace Engineering
M. van Sluis Flight Performance and Propulsion - Aerospace Engineering
Zdobyslaw Goraj Warsaw University of Technology
Mariusz Kowalski Warsaw University of Technology
More Authors... External organisation
Research Group
Flight Performance and Propulsion (Aerospace Engineering) (TU Delft)
Copyright: © 2021 Arne Seitz, Anaïs Luisa Habermann, Fabian Peter, Florian Troeltsch, Alejandro Castillo Pardo, B. della Corte, M. van Sluis, Zdobyslaw Goraj, Mariusz Kowalski, More Authors
DOI: https://doi.org/10.3390/aerospace8010016
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Published Date

2021

Language

English

Faculty

Aerospace Engineering

Department

Flow Physics and Technology

Research Group

Flight Performance and Propulsion

Abstract

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 aerostructural 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%.