Quasi-3D Solutions for Transonic, Inviscid Flows by Adapative Triangulation PUBLIC ACCESS

[+] Author Affiliations
D. Graham Holmes, Scott H. Lamson

GE Research and Development Center, Schenectady, NY

Stuart D. Connell

GE Aircraft Engine Business Group, Cincinnati, OH

Paper No. 88-GT-83, pp. V001T01A037; 9 pages
  • ASME 1988 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 1: Turbomachinery
  • Amsterdam, The Netherlands, June 6–9, 1988
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7918-4
  • Copyright © 1988 by ASME


This paper describes an algorithm for computing two-dimensional transonic, inviscid flows. The solution procedure uses an explicit Runge-Kutta time marching, finite volume scheme. The computational grid is an irregular triangulation. The algorithm can be applied to arbitrary two-dimensional geometries. When used for analyzing flows in blade rows, terms representing the effects of changes in streamsheet thickness and radius, and the effects of rotation, are included. The solution is begun on a coarse grid, and grid points are added adaptively during the solution process, using criteria such as pressure and velocity gradients.

Advantages claimed for this approach are (a) the capability of handling arbitrary geometries (e.g., multiple, dissimilar blades), (b) the ability to resolve small-scale features (e.g., flows around leading edges, shocks) with arbitrary precision, and (c) freedom from the necessity of generating “good” grids (the algorithm generates its own grid, given an initial coarse grid).

Solutions are presented for several examples that illustrate the usefulness of the algorithm.

Copyright © 1988 by ASME
Topics: Inviscid flow
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