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Reduction of Rayleigh Losses in a High G-Loaded Ultra Compact Combustor

[+] Author Affiliations
Jacob D. Wilson, Marc D. Polanka

Air Force Institute of Technology, WPAFB, OH

Paper No. GT2013-94795, pp. V01AT04A057; 9 pages
  • ASME Turbo Expo 2013: Turbine Technical Conference and Exposition
  • Volume 1A: Combustion, Fuels and Emissions
  • San Antonio, Texas, USA, June 3–7, 2013
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-5510-2
  • Copyright © 2013 by ASME


There is a current need to reduce turbine engine system size and weight. An Ultra Compact Combustor (UCC) is a system that attempts to accomplish this by integrating the compressor, combustor, and turbine stages. The main feature of this system is a high gravity-loaded combustor that burns the fuel in the circumferential direction around a hybrid vane row. One consequence of this design is that the UCC needs the combustion process to complete within the vane passage. A second issue is that combining the compressor and turbine results in large flow swirl and high Mach number in the core flow. Combined, these two issues lead to the potential for high Rayleigh losses for this design. This investigation used MATLAB to develop an area ruling inside the passage that allowed the flow to slow to a reasonable Mach number during the heat release process and then accelerate to the desired turbine rotor inlet Mach once combustion has finished. Results showed that it was possible to reduce Rayleigh losses in this manner, but equilibrium between Rayleigh losses and aerodynamic losses must be met. This model was incorporated into a design of a test rig. Reductions of more than 5% in Rayleigh losses in the experimental rig are expected.

Copyright © 2013 by ASME



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