Development of a Hydrogen-powered Fuselage-mounted BLI Propulsor Add-on for Passenger Aircraft

Conference paper (2022)

Authors

A. Heidebrecht Flight Performance and Propulsion - Aerospace Engineering

K.W. Burger Student

M.F.M. Hoogreef Flight Performance and Propulsion - Aerospace Engineering

Roelof Vos Flight Performance and Propulsion - Aerospace Engineering

Askin T. Isikveren SAFRAN S.A. c/o Aerospace Embedded Solutions GmbH

A. Gangoli Rao Flight Performance and Propulsion - Aerospace Engineering

Research Group

Flight Performance and Propulsion (Aerospace Engineering) (TU Delft)

Conceptual aircraft design Boundary Layer Ingestion Hydrogen aircraft

To reference this document use:

http://resolver.tudelft.nl/uuid:b25d2504-e372-41f3-a1b2-8c178dfa704e

More Info

expand_more

Published Date

2022

Language

English

Reuse Rights

Other than for strictly personal use, it is not permitted to download, forward or distribute the text or part of it, without the consent of the author(s) and/or copyright holder(s), unless the work is under an open content license such as Creative Commons.

Faculty

Aerospace Engineering

Department

Flow Physics and Technology

Research Group

Flight Performance and Propulsion

Abstract

The concept of an "Auxiliary Power and Propulsion Unit" (APPU) is introduced, which consists of a Boundarylayer ingesting (BLI) propulsor with an engine mounted at the rear of an passenger aircraft fuselage, replacing the Auxiliary Power Unit (APU) and contributing around 10% of total cruise thrust, as well as auxiliary power. This APPU unit is using hydrogen provided by an additional tank installed in the tailcone of the aircraft. The concept is aimed at lowering the threshold to installing both hydrogen-driven propulsion and BLI propulsors on aircraft in the short term, while minimizing resulting operational risk. The concept has been investigated using a preliminary aircraft synthesis tool and further component-level mass estimates. Operational aspects,
sensitivities and limits to the design have been investigated. Estimates of mission fuel burn find that CO2 emissions emissions reduce roughly proportionally to the APPU thrust share, with additional savings due to improved overall efficiency. Further improvements are deemed feasible and are the topic of ongoing research.

Files

ICAS2022_0622_paper.pdf

(pdf | 0.721 Mb)

Unknown license