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Distributed propulsion and ultra-high by-pass rotor study at aircraft level

Part of: The RAeS Written Paper Prizes 2016

Published online by Cambridge University Press:  27 January 2016

A. T. Isikveren ,
A. Seitz ,
J. Bijewitz ,
A. Mirzoyan ,
A. Isyanov ,
R. Grenon ,
O. Atinault ,
J.-L. Godard  and
S. Stückl
A. Seitz
Affiliation:
Bauhaus Luftfahrt e.V., Ottobrunn, Germany
J. Bijewitz
Affiliation:
Bauhaus Luftfahrt e.V., Ottobrunn, Germany
A. Mirzoyan
Affiliation:
Central Institute of Aviation Motors (CIAM), Moscow, Russia
A. Isyanov
Affiliation:
Central Institute of Aviation Motors (CIAM), Moscow, Russia
R. Grenon
Affiliation:
ONERA – The French Aerospace Lab, Meudon, France
O. Atinault
Affiliation:
ONERA – The French Aerospace Lab, Meudon, France
J.-L. Godard
Affiliation:
ONERA – The French Aerospace Lab, Meudon, France
S. Stückl
Affiliation:
Airbus Group Innovations, Ottobrunn, Germany
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Abstract

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This technical article discusses design and integration associated with distributed propulsion as a means of providing motive power with significantly reduced emissions and external noise for future aircraft concepts. The technical work reflects activities performed within a European Commission funded Framework 7 project entitled Distributed Propulsion and Ultra-high By-Pass Rotor Study at Aircraft Level, or, DisPURSAL. In this instance, the approach of distributed propulsion includes a Distributed Multiple-Fans Concept driven by a limited number of engine cores as well as one unique solution that integrates the fuselage with a single propulsor (dubbed Propulsive-Fuselage Concept) – both targeting entry-in-service year 2035+. Compared to a state-of-the-art, year 2000 reference aircraft, designs with tighter coupling between airframe aerodynamics and motive power system performance for medium-to-long-range operations indicated potentially a 40-45% reduction in CO2-emissions. An evolutionary, year 2035, conventional morphology gas-turbine aircraft was predicted to be –33% in CO2-emissions.

Type
Research Article
Information
The Aeronautical Journal , Volume 119 , Issue 1221 , November 2015 , pp. 1327 - 1376
Copyright
Copyright © Royal Aeronautical Society 2015

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