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research-article

DESIGN AND APPLICATION OF A MULTI-DISCIPLINARY PRE-DESIGN PROCESS FOR NOVEL ENGINE CONCEPTS

[+] Author and Article Information
S. Reitenbach

Institute of Propulsion Technology German Aerospace Center (DLR) Cologne, Germany
stanislaus.reitenbach@dlr.de

A. Krumme

Institute of Propulsion Technology German Aerospace Center (DLR) Cologne, Germany
alexander.krumme@dlr.de

T. Behrendt

Institute of Propulsion Technology German Aerospace Center (DLR) Cologne, Germany
thomas.behrendt@dlr.de

M. Schnös

Institute of Propulsion Technology German Aerospace Center (DLR) Cologne, Germany
markus.schnoes@dlr.de

T. Schmidt

Institute of Structures and Design German Aerospace Center (DLR) Stuttgart, Germany
Thomas.Schmidt@dlr.de

S. Hönig

Institute of Structures and Design German Aerospace Center (DLR) Stuttgart, Germany
sandrine.hoenig@dlr.de

R. Mischke

Simulation and Software Technology German Aerospace Center (DLR) Cologne, Germany
Robert.Mischke@dlr.de

E. Moerland

Institute of Systems Architectures in Aeronautics German Aerospace Center (DLR) Hamburg, Germany
Erwin.Moerland@dlr.de

1Corresponding author.

ASME doi:10.1115/1.4040750 History: Received June 26, 2018; Revised June 29, 2018

Abstract

The purpose of this paper is to present a multi-disciplinary pre-design process and its application to three aero engine models. First, a twin spool mixed flow turbofan engine model is created for validation purposes. The second and third engine models investigated comprise future engine concepts: a Counter Rotating Open Rotor and an Ultra High Bypass Turbofan. The turbofan used for validation is based on publicly available reference data from manufacturing and emission certification. At first the identified interfaces and constraints of the entire pre-design process are presented. An important factor of complexity in this highly iterative procedure is the intricate data flow, as well as the extensive amount of data transferred between all involved disciplines and among different fidelity levels applied within the design phases. To cope with the inherent complexity data modeling techniques have been applied to explicitly determine required data structures of those complex systems. The resulting data model characterizing the components of a gas turbine and their relationships in the design process is presented in detail. Based on the data model the entire engine pre-design process is presented. Starting with the definition of a flight mission scenario and resulting top level engine requirements thermodynamic engine performance models are developed. By means of these thermodynamic models, a detailed engine component pre-design is conducted. The aerodynamic and structural design of the engine components are executed using a stepwise increase in level of detail and are continuously evaluated in context of the overall engine system.

Copyright (c) 2018 by ASME
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