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Conservative Interfacing for Turbomachinery Applications

[+] Author Affiliations
Philip M. Cali

Air Force Research Laboratory, Wright-Patterson Air Force Base, OH

Vincent Couaillier

Office National D’Études et de Recherches Aérospatiales, Châtillon, France

Antony Jameson

Stanford University, Stanford, CA

Paper No. 2001-GT-0357, pp. V001T03A052; 8 pages
doi:10.1115/2001-GT-0357
From:
  • ASME Turbo Expo 2001: Power for Land, Sea, and Air
  • Volume 1: Aircraft Engine; Marine; Turbomachinery; Microturbines and Small Turbomachinery
  • New Orleans, Louisiana, USA, June 4–7, 2001
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7850-7
  • Copyright © 2001 by ASME

abstract

This paper presents the development of a conservative interface technique designed for turbomachinery applications involving multiple rows of blades. Instead of interpolating solution information between blade rows, unique patch boundaries are defined at rotor/stator interfaces on which numerical fluxes are evaluated directly. The fluxes are then distributed to both sides of the interface in a fully conservative fashion. Accuracy is maintained by representing the primitive variables in each interface cell using a system of quadratic polynomials. The coefficients of each polynomial are calculated using neighboring flow information from both sides of the interface. In order to make the reconstruction process more tenable, the current implementation is restricted to pairs of blade rows which maintain identical axisymmetric radial distributions of points at their juncture. Preliminary inviscid flow results show significant improvements in solution quality relative to calculations conducted using conventional nonconservative interpolation techniques.

Copyright © 2001 by ASME
Topics: Turbomachinery

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