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Design and Flow Field Calculations for Transonic and Supersonic Radial Inflow Turbine Guide Vanes FREE

[+] Author Affiliations
A. W. Reichert

Siemens AG, KWU Group, Mülheim, Germany

H. Simon

University of Duisburg, Duisburg, Germany

Paper No. 95-GT-097, pp. V001T01A022; 14 pages
doi:10.1115/95-GT-097
From:
  • ASME 1995 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 1: Turbomachinery
  • Houston, Texas, USA, June 5–8, 1995
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7878-1
  • Copyright © 1995 by ASME

abstract

The design of radial inflow turbine guide vanes depends very much on the discharge conditions desired, especially if the choking mass flow is reached. Because of the choking mass flow condition and supersonic discharge Mach numbers, an inverse design procedure based on the method of characteristics is presented. Various designs which correspond to different discharge Mach numbers are shown. Viscous and inviscid flow field calculations for varying discharge conditions show the properties of the guide vanes at design and off–design conditions.

In a previous paper (Reichert and Simon 1994), an optimized design for transonic discharge conditions has been published. In the present paper, additional results concerning the optimum design are presented. For this optimum design an advantageous adjusting mechanism for a variable geometry guide vane has been developed. The effect of guide vane adjustment on the discharge conditions has been investigated using viscous flow field calculations.

Copyright © 1995 by ASME
This article is only available in the PDF format.

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