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Numerical Computation of the Jet Impingement Cooling of High Pressure Ratio Compressors

[+] Author Affiliations
Elmar Gröschel, Carsten Lipfert, Wolfgang Erb, Daniel Rusch

ABB Turbo Systems AG Schweiz, Baden, Switzerland

Paper No. GT2013-94949, pp. V03BT11A014; 10 pages
  • ASME Turbo Expo 2013: Turbine Technical Conference and Exposition
  • Volume 3B: Heat Transfer
  • San Antonio, Texas, USA, June 3–7, 2013
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-5515-7
  • Copyright © 2013 by ASME


The material temperature field of a centrifugal compressor wheel is one important factor for the life time analysis of a compressor stage. Due to increasing thermal loads of advanced compressor stages, the thermal stresses and/or material temperature levels can exceed the allowed limits for a prescribed exchange interval and cooling techniques are needed to reduce the wheel temperature. One efficient cooling technique is the air impingement cooling. Unlike in gas turbines the impingement cooling is located in the back face region of the compressor wheel. From a computational point of view this means that the impingment jet is located in the stationary frame of reference and the cooled wall is located in the rotating frame of reference. In such a case the heat transfer problem becomes unsteady. The paper introduces a novel CHT-mixing plane interface for the frame change between stationary fluid domain and rotating solid domain to overcome the intrinsic unsteadiness caused by the jet impingement. Fluid mixing plane interfaces between rotor and stator are very common in industries to exploit periodic symmetries and to avoid time consuming unsteady compuations. However, the commercial solvers do not provide a mixing plane interface between fluid and solid domains. First, the new mixing plane approach is validated for a representative test case against a time resolved computation. In the second step, the new method is applied to a compressor stage. Two operating conditions, each with three different cooling mass flows have been computed. The comparison of the wheel temperature field corresponds very well to the computational results for all operating conditions. The temperature field analysis reveals valuable information on the heat transfer in highly loaded compressor stages which can be exploited in the design process of the compressor cooling.

Copyright © 2013 by ASME



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