Change search
ReferencesLink to record
Permanent link

Direct link
Conceptual Design of a 3-shaft Turbofan Engine
Mälardalen University, School of Innovation, Design and Engineering.
Mälardalen University, School of Innovation, Design and Engineering.
2015 (English)Independent thesis Basic level (university diploma), 10 credits / 15 HE creditsStudent thesis
Abstract [en]

During the forthcoming years many new aircrafts such as A350 and B787 are being designed and continually improved. With these new aircrafts and systems, new engines needs to be designed as well, to meet certain requirements such as fuel burn and weight improvement. In this thesis, a baseline engine with technical specifications consistent with a year 2010 EIS has been selected, and the goal was to create a preliminary design of a new engine named AN15 with year entry into service (EIS) 2025 specications. While no mechanical or cost analyses were performed, main emphasis was on thermodynamic and aerodynamic analysis. Literature studies were performed by reading scientific articles combined with books and educational papers. It was very useful and it also let the students know which direction the development of jet engines are going. The thermodynamical analysis was performed in NPSS (Numerical Propulsion System Simulation). A code, written in C++, was produced in order to fit the requirements of a 3-shafted turbofan engine and with the acquired knowledge from the literature studies it was thermodynamically analysed. The thermodynamical analysis included optimizing parameters such as temperatures and pressure ratios to have an engine as efficient as possible. Once the thermodynamical analysis was done, MATLAB was used to write a script which covered the aerodynamical design such as plotting aspects as well as calculations which were available from open literatures. Velocity triangles for compressor and turbine components in the engine was also generated through the MATLAB script. The result was a 3-shafted turbofan jet engine which had almost the same length as the baseline engine, a 21% larger fan diameter and a fuel burn improvement of 11% compared to the baseline engine. Some of the main conclusions were that propulsive efficiency was increased, but also that the development is going towards jet engine designs with lower fuel consumption.

Place, publisher, year, edition, pages
2015. , 50 p.
Keyword [en]
Concept, Design, Turbofan, Shaft, Airplane, Fan, Fuel, Emissions, Optimization
National Category
Engineering and Technology
URN: urn:nbn:se:mdh:diva-28223OAI: diva2:820082
Subject / course
Aeronautical Engineering
Available from: 2015-06-30 Created: 2015-06-11 Last updated: 2015-06-30Bibliographically approved

Open Access in DiVA

fulltext(3136 kB)203 downloads
File information
File name FULLTEXT01.pdfFile size 3136 kBChecksum SHA-512
Type fulltextMimetype application/pdf

By organisation
School of Innovation, Design and Engineering
Engineering and Technology

Search outside of DiVA

GoogleGoogle Scholar
Total: 203 downloads
The number of downloads is the sum of all downloads of full texts. It may include eg previous versions that are now no longer available

Total: 198 hits
ReferencesLink to record
Permanent link

Direct link