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Numerical Calculation of Three-Dimensional Euler Flow Through a Transonic Test Turbine Stage FREE

[+] Author Affiliations
Harald Paßrucker, Wolfgang Sanz, Herbert Jericha

Graz University of Technology, Graz, Austria

Paper No. 98-GT-428, pp. V001T01A103; 8 pages
doi:10.1115/98-GT-428
From:
  • ASME 1998 International Gas Turbine and Aeroengine Congress and Exhibition
  • Volume 1: Turbomachinery
  • Stockholm, Sweden, June 2–5, 1998
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7862-0
  • Copyright © 1998 by ASME

abstract

The objective of this work is the development of an implicit block-structured central-differencing scheme with implicit treatment of the boundary conditions for the calculation of three-dimensional inviscid compressible steady flow, primarily through transonic turbomachinery stages. The implicit boundary treatment is based on the mathematical theory of characteristics for hyperbolic systems of equations. Steady-state non-reflecting boundary conditions at the inflow and outflow boundaries and at the stator/rotor interface based on Fourier analysis applied to the linearized Euler equations are also used. Getting a monotonous resolution of shocks, a non-linear additive viscosity term of 2nd and 4th order with pressure-controlled factors is implemented. The three-dimensional blade geometry consists of Bézier-surfaces which are determined by two-dimensional blade profiles based on Bézier-curves. The grid for the flow calculation is obtained by parameterizing special Bézier-surfaces, respectively Bézier-volumes. Finally, the aerodynamic design of the one-stage highly loaded transonic test turbine of Institute of Thermal Turbomachinery and Machine Dynamics - Graz University of Technology) with these tools described above is illustrated with detailed presentation of the specific aerodynamic features, the design technology and the computational results.

Copyright © 1998 by ASME
This article is only available in the PDF format.

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