The Influence of Blade Leaning on the Performance of an Integrated OGV-Diffuser System PUBLIC ACCESS

[+] Author Affiliations
J. F. Carrotte, S. J. Stevens, A. P. Wray

University of Technology, Loughborough, England

Paper No. 91-GT-104, pp. V001T01A046; 9 pages
  • ASME 1991 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 1: Turbomachinery
  • Orlando, Florida, USA, June 3–6, 1991
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7898-9
  • Copyright © 1991 by ASME


An experimental investigation has been carried out to study the performance of an integrated design of compressor outlet guide vane and combustor pre-diffuser system. The trailing edge of each OGV was located within the outwardly canted diffuser by a distance equal to 27% of the diffuser axial length. In order to obtain representative inlet conditions a rotor, providing a fully sheared velocity profile and an air outlet angle of approximately 40°, was located upstream of the OGVs. Compared with the measured performance when the trailing edge of each OGV was located at diffuser inlet, a small increase in total pressure loss and a corresponding decrease in static pressure recovery was observed for the shortened system. This change in performance reflected a deterioration in the flow conditions along the outer wall, with transitory stalling of the flow being observed at diffuser exit. By leaning the blades in a circumferential direction through angles of 10° and 15° the outer wall flow conditions could be progressively improved, although at the largest angle tested stalling of the flow occurred at the hub of each OGV. However, at a lean angle of 10° the performance, in terms of loss and flow stability, could be virtually restored to the levels obtained when the trailing edge of each OGV was located radially at diffuser inlet.

Copyright © 1991 by ASME
Topics: Diffusers , Blades
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