Design and Development of the Combustor Inlet Diffuser for the NASA/GE Energy Efficient Engine FREE

[+] Author Affiliations
P. E. Sabla, J. R. Taylor

General Electric Co., Evendale, OH

D. J. Gauntner

NASA Lewis Research Center, Cleveland, OH

Paper No. 81-GT-129, pp. V002T06A025; 9 pages
  • ASME 1981 International Gas Turbine Conference and Products Show
  • Volume 2: Coal, Biomass and Alternative Fuels; Combustion and Fuels; Oil and Gas Applications; Cycle Innovations
  • Houston, Texas, USA, March 9–12, 1981
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7962-7
  • Copyright © 1981 by ASME


Results of an experimental investigation of the aerodynamic performance of a split duct annular combustor inlet diffuser system are presented. Several diffuser configurations were investigated in 3X-scale water table tests and the preferred design was evaluated in full-scale annular airflow model tests. Pressure recovery and flow losses were determined as a function of prediffuser inlet velocity profile, flow extraction at the prediffuser exit, and distribution of flow in the combustor. Inlet velocity profile and turbulence levels were found to have a pronounced effect on system performance. Flow extraction at the prediffuser exit was found to have little influence on system performance. Generally, the annular split duct diffuser system was found to satisfy the performance objectives for the engine.

Copyright © 1981 by ASME
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