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Study and Experiments of a Small Radial Turbine for Auxiliary Power Units FREE

[+] Author Affiliations
Y. Ribaud

National d’Etudes et de Recherches Aérospatiales, Chatillon, France

C. Mischel

MICROTURBO, Toulouse, France

Paper No. 86-GT-23, pp. V002T04A003; 8 pages
doi:10.1115/86-GT-23
From:
  • ASME 1986 International Gas Turbine Conference and Exhibit
  • Volume 2: Aircraft Engine; Marine; Microturbines and Small Turbomachinery
  • Dusseldorf, West Germany, June 8–12, 1986
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7929-0
  • Copyright © 1986 by ASME

abstract

The design of a small inward flow turbine with a 3.6 expansion ratio has been undertaken by MICROTURBO, in cooperation with ONERA for calculations and test results analysis.

Initially, the purpose and constraints of this study are underlined. Preliminary calculations have led to the design of the blade shape of the Nozzle Guide Vane and of the rotor. Following this, the results of the quasi-3D-flow computations, performed for the stator and the rotor, are given. Both the cold bench tests on this turbine and the corresponding hot tests on the turboshaft engine enable performances to be checked. The value of the calculations is confirmed when we look at the high total and static adiabatic efficiencies obtained. These good results are encouraging for the future use of this kind of turbomachine.

Copyright © 1986 by ASME
Topics: Turbines
This article is only available in the PDF format.

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