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Preliminary Engine Design for the MULDICON Configuration

Zenkner, Sebastian and Becker, Richard-Gregor (2018) Preliminary Engine Design for the MULDICON Configuration. AIAA Aviation Forum, 2018-06-25 - 2018-06-29, Atlanta, Georgia, USA. doi: 10.2514/6.2018-3163.

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The present paper describes the preliminary engine design efforts for the Muldicon UCAV configuration. As a first step, a thermodynamic model of a two shaft mixed flow turbofan engine was created. In order to improve the fundamental cycle design parameters such as bypass ratio, fan pressure ratio, overall pressure ratio an automated multi objective optimization process was applied. Therein, the first objective was to minimize the amount of fuel needed for the given design mission of the Muldicon configuration. As a second figure of merit a minimal fan diameter was used. On basis of the thermodynamic parameters of each optimization member preliminary flow path sketches of the turbo components have been carried out to estimate the engine geometry. The optimization was subject to several constraints, such as maximum material temperatures, maximum mechanical speeds or aerodynamic loading of the turbo components. The optimization process and the final design are presented and discussed in detail.

Item URL in elib:https://elib.dlr.de/121002/
Document Type:Conference or Workshop Item (Speech)
Title:Preliminary Engine Design for the MULDICON Configuration
AuthorsInstitution or Email of AuthorsAuthor's ORCID iDORCID Put Code
Zenkner, SebastianUNSPECIFIEDhttps://orcid.org/0000-0002-7279-591XUNSPECIFIED
Date:26 June 2018
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In ISI Web of Science:No
Keywords:engine performance, aero engine cycle, performance optimization, UCAV, Fan diameter
Event Title:AIAA Aviation Forum
Event Location:Atlanta, Georgia, USA
Event Type:international Conference
Event Start Date:25 June 2018
Event End Date:29 June 2018
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 (old)
Location: Köln-Porz
Institutes and Institutions:Institute of Propulsion Technology
Institute of Propulsion Technology > Engine
Deposited By: Zenkner, Sebastian
Deposited On:17 Jul 2018 15:10
Last Modified:24 Apr 2024 20:25

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