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3D CFD Compressor Map Computation Process Accounting for Geometry Changes due to Off-Design Operation Loads

[+] Author Affiliations
Christian Janke, Kai Karger, Lilia Gaun, Dieter Bestle

Brandenburg University of Technology, Cottbus, Germany

André Huppertz

Rolls-Royce Deutschland Ltd & Co KG, Blankenfelde-Mahlow, Germany

Paper No. GT2014-26131, pp. V02BT39A023; 12 pages
  • ASME Turbo Expo 2014: Turbine Technical Conference and Exposition
  • Volume 2B: Turbomachinery
  • Düsseldorf, Germany, June 16–20, 2014
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-4561-5
  • Copyright © 2014 by Rolls-Royce Deutschland Ltd & Co KG


Compressor maps of aero engines show the relation between corrected inlet mass flow and total pressure ratio for various engine speeds. Different speed lines represent different operating conditions of the compressor, where especially operating bounds like surge and choke are important for the design process. Typically, 3D CFD compressor maps are computed with the so called hot geometry given for the aerodynamic design point. However, in reality airfoil shapes will change for different engine speeds and gas loads resulting in twisted airfoils and changed tip clearances. Thus, using the nominal hot geometry for the whole compressor map is not fully correct. In order to obtain higher quality performance maps these effects need to be considered. The paper shows a process for computing compressor maps with 3D CFD, where strucural deformations of the blade due to varying speeds and gas loads are taken into account by blade morphing. This process is applied to a 1.5-stage compressor showcase.

Copyright © 2014 by Rolls-Royce Deutschland Ltd & Co KG



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