QUASI THREE DIMENSIONAL COMPRESSOR DESIGN FOR A TWIN-SPOOL LOW BYPASS RATIO TURBOFAN ENGINE

Authors

  • Serdar Duman
  • Onur Tunçer

Keywords:

Compressor design, Blade airfoil, Compressor aerodynamics

Abstract

This paper presents the preliminary design of a three stage fan for a twin-spool low bypass ratio turbofan aeroengine. Design produre 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.

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References

[1] S. Duman, Parametric cycle analysis and fan design for a low bypass ratio gas turbine, June 2010, Graduation Thesis, Istanbul Technical University, Istanbul.
[2] S. Duman and O. Tuncer, Görev Analizi Sonucu Bir Savaş Uçağının Motor İtki gereksiniminin Belirlenmesi, Havacılık ve Uzay Teknolojileri Dergisi, vol. 5, no.1, pp. 27-38, January 2011.
[3] S. L. Dixon and C.A. Hall, Fluid Mechanics and Thermodynamics of Turbomachinery, Butterworth-Heinemann, 2010.
[4] J. D. Mattingly and H. von Ohain, Elements of Propulsion: Gas Turbines and Rockets, AIAA Education Series. AIAA, August 2006.
[5] J. D. Mattingly, W. Heiser, and D. Pratt, Aircraft Engine Design, AIAA Education Series. AIAA, second edition, August 2006.
[6] A.B. McKenzie, Axial Flow Fans and Compressors: Aerodynamic Design and Performance, Cranfield Series on Turbomachinery Technology. Ashgate Publishing, July 1997.
[7] Paul Jackson, Kenneth Munson, and Lindsay Peacock, Jane’s All the World’s Aircraft 2008-2009, Jane’s Information Group, June 2008.
[8] O. Bill and F. Gunston, Jane’s Aeroengines, Jane’s Information Group, January 2008.
[9] N. Chen, Aerothermodynamics of Turbomachinery: Analysis and Design, Wiley, June 2010.

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Published

23-01-2012

How to Cite

[1]
S. Duman and O. Tunçer, “QUASI THREE DIMENSIONAL COMPRESSOR DESIGN FOR A TWIN-SPOOL LOW BYPASS RATIO TURBOFAN ENGINE”, JAST, vol. 5, no. 3, pp. 1–7, Jan. 2012.

Issue

Vol. 5 No. 3 (2012)

Section

Articles

License

The manuscript with title and authors is being submitted for publication in Journal of Aeronautics and Space Technologies. This article or a major portion of it was not published, not accepted and not submitted for publication elsewhere. If accepted for publication, I hereby grant the unlimited and all copyright privileges to Journal of Aeronautics and Space Technologies.

I declare that I am the responsible writer on behalf of all authors.