elib
DLR-Header
DLR-Logo -> http://www.dlr.de
DLR Portal Home | Imprint | Privacy Policy | Contact | Deutsch
Fontsize: [-] Text [+]

Preliminary engine design and inlet optimization of the MULDICON concept

Zenkner, Sebastian and Trost, Marco and Becker, Richard-Gregor and Voß, Christian (2019) Preliminary engine design and inlet optimization of the MULDICON concept. Aerospace Science and Technology, 93 (105318). Elsevier. DOI: 10.1016/j.ast.2019.105318 ISSN 1270-9638

[img] PDF - Registered users only - Preprint version (submitted draft)
592kB

Official URL: https://doi.org/10.1016/j.ast.2019.105318

Abstract

In this study, aspects of the propulsion design for a highly swept wing configuration with military application are presented. These include the design of the thermodynamic cycle and the automated optimization of the inlet geometry. First, the thermodynamic design process of a conventional turbofan engine is described, which is intended to meet the requirements of a generic UCAV configuration. In addition to the thrust requirements derived from the mission profile, other constraints such as maximum fuel consumption, available installation space and aerodynamic and structural limits dimension the model in preliminary design. The resulting engine data are used as boundary conditions for the CFD simulation of the associated engine intake. This CFD calculation is part of an optimization process chain for determining the inlet duct geometry with low total pressure loss and low engine visibility. In order to estimate the effects of the different total pressure losses on the mission fuel consumption, the results obtained using CFD calculations are fed back into the performance simulation. This allows quantifying the influence of the inlet geometry on the global engine parameter. Based on the investigations and obtained results, the final configurations for the engine and intake are selected.

Item URL in elib:https://elib.dlr.de/133397/
Document Type:Article
Title:Preliminary engine design and inlet optimization of the MULDICON concept
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Zenkner, SebastianSebastian.Zenkner (at) dlr.deUNSPECIFIED
Trost, MarcoMarco.Trost (at) dlr.deUNSPECIFIED
Becker, Richard-GregorRichard-Gregor.Becker (at) dlr.deUNSPECIFIED
Voß, ChristianChristian.Voss (at) dlr.deUNSPECIFIED
Date:October 2019
Journal or Publication Title:Aerospace Science and Technology
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In SCOPUS:Yes
In ISI Web of Science:Yes
Volume:93
DOI :10.1016/j.ast.2019.105318
Publisher:Elsevier
Series Name:Aerospace Science and Technology
ISSN:1270-9638
Status:Published
Keywords:aircraft engine performance; engine inlet duct geometry; geometry optimization; inlet distortion; UCAV
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Aeronautics
HGF - Program Themes:fixed-wing aircraft
DLR - Research area:Aeronautics
DLR - Program:L AR - Aircraft Research
DLR - Research theme (Project):L - Military Technologies
Location: Köln-Porz
Institutes and Institutions:Institute of Propulsion Technology > Engine
Institute of Propulsion Technology > Fan and Compressor
Deposited By: Zenkner, Sebastian
Deposited On:13 Jan 2020 09:28
Last Modified:13 Jan 2020 09:28

Repository Staff Only: item control page

Browse
Search
Help & Contact
Information
electronic library is running on EPrints 3.3.12
Copyright © 2008-2017 German Aerospace Center (DLR). All rights reserved.