We found a match
Your institution may have access to this item. Find your institution then sign in to continue.
- Title
QUASI THREE DIMENSIONAL COMPRESSOR DESIGN FOR A TWIN-SPOOL LOW BYPASS RATIO TURBOFAN ENGINE.
- Authors
Duman, Serdar; Tunçer, Onur
- Abstract
This paper presents the preliminary design of a three-stage fan for a twin-spool low bypass ratio turbofan aeroengine. Design produce has been initialized with the specification of technical requirements obtained from the parametric cycle analysis. With this information, a suitable baseline engine is selected that has the closest technical specifications. The design process continues with the determination of the number of fan stages and other stage parameters. The next step is the designation of the blade airfoil profiles such that they have adequate stall margin in subsonic conditions. Airfoils are designed to avoid both positive and negative stall situations. Hub profiles have noticeably larger cambers due to lower linear speeds in comparison to tip profiles. By stacking up airfoil profiles in the radial direction form hub to tip a quasi three-dimensional design is reached. Finally, solid models of the rotor and the stator parts were produced.
- Subjects
AIRPLANE turbofan engine design &; construction; COMPRESSORS; AERONAUTICS; AEROSPACE engineering; AEROFOILS; AIRPLANE turbofan engine blades; STATORS
- Publication
Journal of Aeronautics & Space Technologies / Havacilik ve Uzay Teknolojileri Dergisi, 2012, Vol 5, Issue 3, p1
- ISSN
1304-0448
- Publication type
Article